Airworthiness Directives; Viking Air Limited Model DHC-7 Airplanes, 32434-32436 [06-5119]
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32434
Federal Register / Vol. 71, No. 108 / Tuesday, June 6, 2006 / Rules and Regulations
TABLE 2.—ENGINES INSTALLED ON, BUT NOT LIMITED TO—Continued
IO–540–W3A5D .................
AEIO–540–D4A5 ................
AEIO–540–D4B5 ................
AEIO–540–D4D5 ................
TIO–540–C1A .....................
TIO–540–K1AD ..................
TIO–540–AA1AD ................
TIO–540–AB1AD ................
TIO–540–AB1BD ................
TIO–540–AF1A ...................
TIO–540–AG1A ..................
TIO–540–AK1A ..................
LTIO–540–K1AD ................
Schweizer: Power Glider.
Christen: Pitts (S–2S), (S–2B).
Siai-Marchetti: SF–260.
H.A.L.: HPT–32.
Slingsby: Firefly T3A.
Moravan: Zlin-50L.
H.A.L.: HPT–32.
Burkhart Grob: Grob G, 115T Aero.
Piper Aircraft: Turbo Aztec (PA–23–250).
Piper Aircraft.
Aerofab Inc.: Turbo Renegade (270).
S.O.C.A.T.A.: Trinidad TC TB–21.
Schweizer.
Mooney Aircraft: ‘‘TLS’’ M20M.
Commander Aircraft: 114TC.
Cessna Aircraft: Turbo Skylane T182T.
Piper Aircraft.
Unsafe Condition
(d) This AD results from reports of
applicability errors found in AD 2005–26–10.
We are issuing this AD to prevent loss of
engine power due to cracks in the cylinder
assemblies and possible engine failure
caused by separation of a cylinder head.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified unless the
actions have already been done.
wwhite on PROD1PC61 with RULES
Engines Not Overhauled or Repaired Since
New
(f) If your engine has not been overhauled
or had any major repair since new, no further
action is required.
Engines Overhauled or Repaired Since New
(g) If your engine was overhauled or
repaired since new, do the following:
(1) Determine if ECi cylinder assemblies,
P/N AEL65102 series ‘‘Classic Cast’’, having
casting head markings EC 65099–REV–1 and
SNs 1 through 9879 (SN may have an ‘‘L’’
prefix for a long reach spark plug) are
installed on your engine, as follows:
(i) Inspect the engine log books and
maintenance records for reference to the
subject ECi cylinder assemblies.
(ii) If the engine log books and
maintenance records did not record the P/N
and SN of the cylinder assemblies, visually
inspect the cylinder assemblies and verify
the P/N and SN of the cylinder assemblies.
(2) If the cylinder assemblies are not ECi,
P/N AEL65102 series ‘‘Classic Cast’’, having
casting head markings EC 65099–REV–1, no
further action is required.
(3) If any cylinder assembly is an ECi
P/N AEL65102 series ‘‘Classic Cast’’, having
casting head markings EC 65099–REV–1 and
a SN 1 through 9879 (SN may have an ‘‘L’’
prefix for a long reach spark plug), do the
following:
(i) If the cylinder assembly has fewer than
800 operating hours-in-service (HIS) on the
effective date of this AD, replace the cylinder
assembly at no later than 800 operating HIS.
No action is required until the operating HIS
reaches 800 hours.
(ii) If the cylinder assembly has 800
operating HIS or more on the effective date
VerDate Aug<31>2005
16:35 Jun 05, 2006
Jkt 208001
of this AD, replace the cylinder assembly
within 60 operating HIS after the effective
date of this AD.
Definition of a Replacement Cylinder
Assembly
(h) For the purpose of this AD, a
replacement cylinder assembly is defined as
follows:
(1) A serviceable cylinder assembly made
by Lycoming Engines.
(2) A serviceable FAA-approved, Parts
Manufacturer Approval cylinder assembly
from another manufacturer.
(3) A serviceable ECi cylinder assembly,
P/N AEL65102 series, ‘‘Titan’’, having casting
P/N AEL85099.
(4) A serviceable ECi cylinder assembly,
P/N AEL65102 series ‘‘Classic Cast’’, having
casting head markings EC 65099–REV–1, that
has a SN 9880 or higher (SN may have an ‘‘L’’
prefix for a long reach spark plug).
Prohibition of Cylinder Assemblies, P/N
AEL65102 Series ‘‘Classic Cast’’, Having
Casting Head Markings EC 65099–REV–1
and SNs 1 Through 9879
(i) After the effective date of this AD, do
not install any ECi cylinder assembly, P/N
AEL65102, having casting head markings EC
65099–REV–1 that has a SN 1 through 9879
(SN may have an ‘‘L’’ prefix for a long reach
spark plug), onto any engine.
Alternative Methods of Compliance
(j) The Manager, Special Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Related Information
(k) ECi Service Bulletin No. 05–08,
Revision 2, dated February 28, 2006, pertains
to the subject of this AD.
Issued in Burlington, Massachusetts, on
May 31, 2006.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 06–5127 Filed 6–5–06; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24966; Directorate
Identifier 2006–NM–049–AD; Amendment
39–14629; AD 2006–12–04]
RIN 2120–AA64
Airworthiness Directives; Viking Air
Limited Model DHC–7 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Viking Air Limited Model DHC–7
airplanes. This AD requires revising the
FAA-approved Airworthiness
Limitations section of the airplane
maintenance manual to prohibit
operation of the airplane past its
designed life limit for the primary
structure, which is 80,000 total flight
cycles. This AD also requires contacting
the FAA for approval of analysis that
substantiates that the airplane is safe to
continue operation beyond the designed
life limit. This AD results from a report
that the designed life limit for the
primary structure for the affected
airplanes is 80,000 total flight cycles.
We are issuing this AD to prevent
continued operation of an airplane
beyond its designed life limit for the
primary structure, which could result in
reduced structural integrity of the
airplane.
This AD becomes effective June
21, 2006.
We must receive comments on this
AD by August 7, 2006.
DATES:
E:\FR\FM\06JNR1.SGM
06JNR1
Federal Register / Vol. 71, No. 108 / Tuesday, June 6, 2006 / Rules and Regulations
Use one of the following
addresses 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.
• Fax: (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.
FOR FURTHER INFORMATION CONTACT:
George Duckett, Aerospace Engineer,
Airframe and Propulsion Branch, ANE–
171, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, suite 410, Westbury, New York
11590; telephone (516) 228–7325; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
ADDRESSES:
Discussion
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
authority for Canada, notified us that an
unsafe condition may exist on certain
Viking Air Limited Model DHC–7
airplanes. TCCA advises that the
designed life limit for the primary
structure for the affected airplanes is
80,000 total flight cycles. TCCA states
that the operator’s approved
maintenance schedule should be revised
to prohibit operators from flying the
airplane after it reaches its design goal,
unless the operator complies with
further inspections and/or
modifications. Continued operation of
an airplane beyond its designed life
limit for the primary structure, if not
corrected, could result in reduced
structural integrity of the airplane.
TCAA issued Canadian airworthiness
directive CF–2005–36, dated September
28, 2005, to ensure the continued
airworthiness of these airplanes in
Canada.
wwhite on PROD1PC61 with RULES
FAA’s Determination and Requirements
of This AD
This airplane model is manufactured
in Canada and is type certificated for
operation in the United States under the
provisions of section 21.29 of the
Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
airworthiness agreement. Pursuant to
this bilateral airworthiness agreement,
VerDate Aug<31>2005
16:35 Jun 05, 2006
Jkt 208001
the TCCA has kept the FAA informed of
the situation described above. We have
examined the TCCA’s findings,
evaluated all pertinent information, and
determined that we need to issue an AD
for products of this type design that are
certificated for operation in the United
States.
Therefore, we are issuing this AD,
which would require revising the
Airworthiness Limitations section of the
Bombardier DHC–7 Dash 7 maintenance
manual and the Dash 7 Series 150
maintenance manual to prohibit
operation of the airplane past its
designed life limit for the primary
structure, which is 80,000 total flight
cycles. This AD also requires contacting
the FAA for approval to continue
operation beyond the designed life
limit.
Differences Between This AD and the
Canadian Airworthiness Directive
The Canadian airworthiness directive
specifies that operators should ground
airplanes that have reached the
designed life limit until operators
provide data to substantiate compliance
with Canadian Airworthiness
Regulation CAR 511.34. This AD
requires that operators contact the FAA
to substantiate continued safe operation
beyond the designed life limit of 80,000
total flight cycles.
Costs of Compliance
None of the airplanes affected by this
action are on the U.S. Register. All
airplanes affected by this AD are
currently operated by non-U.S.
operators under foreign registry;
therefore, they are not directly affected
by this AD action. However, we
consider this AD necessary to ensure
that the unsafe condition is addressed if
any affected airplane is imported and
placed on the U.S. Register in the future.
If an affected airplane is imported and
placed on the U.S. Register in the future,
the required AMM revision will take
about 1 work hour per airplane at an
average labor rate of $80 per work hour.
Based on these figures, the cost of the
AMM revision for U.S. operators will be
$80 per airplane. We recognize that this
AD may impose certain additional
operational costs. However, we cannot
calculate those costs because we cannot
predict the extent of any necessary
repairs to ensure the continued
airworthiness of the affected airplanes.
FAA’s Determination of the Effective
Date
No airplane affected by this AD is
currently on the U.S. Register.
Therefore, providing notice and
opportunity for public comment is
PO 00000
Frm 00021
Fmt 4700
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32435
unnecessary before this AD is issued,
and this AD may be made effective in
less than 30 days after it is published in
the Federal Register.
Comments Invited
This AD is a final rule that involves
requirements that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
relevant written data, views, or
arguments regarding this AD. Send your
comments to an address listed in the
ADDRESSES section. Include ‘‘Docket No.
FAA–2006–24966; Directorate Identifier
2006–NM–049–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD that might suggest a
need to modify it.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of that Web site, anyone
can find and read the comments in any
of our dockets, including the name of
the individual who sent the comment
(or signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
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
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06JNR1
32436
Federal Register / Vol. 71, No. 108 / Tuesday, June 6, 2006 / Rules and Regulations
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this 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 the regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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 Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
wwhite on PROD1PC61 with RULES
I
2006–12–04 Viking Air Limited (Formerly
Bombardier, Inc.): Amendment 39–
14629. Docket No. FAA–2006–24966;
Directorate Identifier 2006–NM–049–AD.
Effective Date
(a) This AD becomes effective June 21,
2006.
VerDate Aug<31>2005
16:35 Jun 05, 2006
Jkt 208001
Affected ADs
Material Incorporated by Reference
(k) None.
(b) None
Applicability
(c) This AD applies to Viking Air Limited
Model DHC–7–1, DHC–7–100, DHC–7–101,
DHC–7–102, and DHC–7–103 airplanes,
certificated in any category; except airplanes
having serial numbers 3 through 10
inclusive, 12 through 14 inclusive, and 16
through 27 inclusive.
Issued in Renton, Washington, on May 31,
2006.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–5119 Filed 6–5–06; 8:45 am]
BILLING CODE 4910–13–P
Unsafe Condition
(d) This AD results from a report that the
designed life limit for the primary structure
for the affected airplanes is 80,000 total flight
cycles. We are issuing this AD to prevent
continued operation of an airplane beyond its
designed life limit for the primary structure,
which could result in reduced structural
integrity of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Airworthiness Limitations Revision
(f) Within 30 days after the effective date
of this AD: Revise the FAA-approved
Airworthiness Limitations section (ALS) of
the Bombardier DHC–7 Dash 7 maintenance
manual and the Dash 7 Series 150
maintenance manual to state the following
(this may be done by inserting a copy of this
AD into the ALS). Thereafter, maintain the
airplane in accordance with the limitations
specified in these maintenance manual
revisions:
‘‘Do not operate the airplane beyond
80,000 total flight cycles.’’
(g) When the statement specified in
paragraph (f) of this AD has been included
in the general revisions of the ALS, the
general revisions may be incorporated into
the ALS and the copy of the AD may be
removed from the ALS.
(h) The airworthiness limitation specified
in paragraph (f) of this AD may be removed
from the maintenance manuals specified in
paragraph (f) of this AD after the Manager,
New York Aircraft Certification Office (ACO),
FAA, approves analysis that substantiates
continued safe operation beyond the
designed life limit of 80,000 total flight
cycles.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, New York ACO, FAA,
has the authority to approve AMOCs for this
AD, if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Related Information
(j) Canadian airworthiness directive CF–
2005–36, dated September 28, 2005, also
addresses the subject of this AD.
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DEPARTMENT OF HEALTH AND
HUMAN SERVICES
Food and Drug Administration
21 CFR Part 522
Implantation or Injectable Dosage
Form New Animal Drugs;
Oxytetracycline Injection, 200
Milligram/Milliliter
AGENCY:
Food and Drug Administration,
HHS.
Final rule; technical
amendment.
ACTION:
SUMMARY: The Food and Drug
Administration (FDA) is amending the
animal drug regulations to correct the
indications for use for the 200 milligram
(mg)/milliliter (mL) strength of
oxytetracycline injectable solution used
in beef cattle for the treatment and
control of various bacterial diseases.
This action is being taken to improve
the accuracy of the regulations.
DATES: This rule is effective June 6,
2006.
FOR FURTHER INFORMATION CONTACT:
George K. Haibel, Center for Veterinary
Medicine (HFV–6), Food and Drug
Administration, 7519 Standish Pl.,
Rockville, MD 20855, 240–276–9019, email: george.haibel@fda.hhs.gov.
SUPPLEMENTARY INFORMATION: FDA has
found that the April 1, 2005, edition of
Title 21 parts 500 to 599 of the Code of
Federal Regulations (CFR) does not
accurately reflect the approved
indications for use for the 200 mg/mL
strength of oxytetracycline injectable
solution. Certain indications of use for
the 300 mg/mL strength of
oxytetracycline injectable solution
appear to have been included as an error
in the section for the 200 mg/mL
strength solution during reformatting
(69 FR 31878, June 8, 2004). At this
time, FDA is amending the regulations
in 21 CFR 522.1660a to reflect the
correct approved indications for use.
This action is being taken to improve
the accuracy of the regulations.
This rule does not meet the definition
of ‘‘rule’’ in 5 U.S.C. 804(3)(A) because
it is a rule of ‘‘particular applicability.’’
E:\FR\FM\06JNR1.SGM
06JNR1
]]>Agencies
[Federal Register Volume 71, Number 108 (Tuesday, June 6, 2006)]
[Rules and Regulations]
[Pages 32434-32436]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5119]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24966; Directorate Identifier 2006-NM-049-AD;
Amendment 39-14629; AD 2006-12-04]
RIN 2120-AA64
Airworthiness Directives; Viking Air Limited Model DHC-7
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Viking Air Limited Model DHC-7 airplanes. This AD requires
revising the FAA-approved Airworthiness Limitations section of the
airplane maintenance manual to prohibit operation of the airplane past
its designed life limit for the primary structure, which is 80,000
total flight cycles. This AD also requires contacting the FAA for
approval of analysis that substantiates that the airplane is safe to
continue operation beyond the designed life limit. This AD results from
a report that the designed life limit for the primary structure for the
affected airplanes is 80,000 total flight cycles. We are issuing this
AD to prevent continued operation of an airplane beyond its designed
life limit for the primary structure, which could result in reduced
structural integrity of the airplane.
DATES: This AD becomes effective June 21, 2006.
We must receive comments on this AD by August 7, 2006.
[[Page 32435]]
ADDRESSES: Use one of the following addresses 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.
Fax: (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.
FOR FURTHER INFORMATION CONTACT: George Duckett, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New
York 11590; telephone (516) 228-7325; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada Civil Aviation (TCCA), which is the airworthiness
authority for Canada, notified us that an unsafe condition may exist on
certain Viking Air Limited Model DHC-7 airplanes. TCCA advises that the
designed life limit for the primary structure for the affected
airplanes is 80,000 total flight cycles. TCCA states that the
operator's approved maintenance schedule should be revised to prohibit
operators from flying the airplane after it reaches its design goal,
unless the operator complies with further inspections and/or
modifications. Continued operation of an airplane beyond its designed
life limit for the primary structure, if not corrected, could result in
reduced structural integrity of the airplane.
TCAA issued Canadian airworthiness directive CF-2005-36, dated
September 28, 2005, to ensure the continued airworthiness of these
airplanes in Canada.
FAA's Determination and Requirements of This AD
This airplane model is manufactured in Canada and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the TCCA has kept the FAA informed
of the situation described above. We have examined the TCCA's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for products of this type design that are certificated for
operation in the United States.
Therefore, we are issuing this AD, which would require revising the
Airworthiness Limitations section of the Bombardier DHC-7 Dash 7
maintenance manual and the Dash 7 Series 150 maintenance manual to
prohibit operation of the airplane past its designed life limit for the
primary structure, which is 80,000 total flight cycles. This AD also
requires contacting the FAA for approval to continue operation beyond
the designed life limit.
Differences Between This AD and the Canadian Airworthiness Directive
The Canadian airworthiness directive specifies that operators
should ground airplanes that have reached the designed life limit until
operators provide data to substantiate compliance with Canadian
Airworthiness Regulation CAR 511.34. This AD requires that operators
contact the FAA to substantiate continued safe operation beyond the
designed life limit of 80,000 total flight cycles.
Costs of Compliance
None of the airplanes affected by this action are on the U.S.
Register. All airplanes affected by this AD are currently operated by
non-U.S. operators under foreign registry; therefore, they are not
directly affected by this AD action. However, we consider this AD
necessary to ensure that the unsafe condition is addressed if any
affected airplane is imported and placed on the U.S. Register in the
future.
If an affected airplane is imported and placed on the U.S. Register
in the future, the required AMM revision will take about 1 work hour
per airplane at an average labor rate of $80 per work hour. Based on
these figures, the cost of the AMM revision for U.S. operators will be
$80 per airplane. We recognize that this AD may impose certain
additional operational costs. However, we cannot calculate those costs
because we cannot predict the extent of any necessary repairs to ensure
the continued airworthiness of the affected airplanes.
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register.
Therefore, providing notice and opportunity for public comment is
unnecessary before this AD is issued, and this AD may be made effective
in less than 30 days after it is published in the Federal Register.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2006-
24966; Directorate Identifier 2006-NM-049-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of that Web
site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
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
[[Page 32436]]
section, Congress charges the FAA with promoting safe flight of civil
aircraft in air commerce by prescribing regulations for practices,
methods, and procedures the Administrator finds necessary for safety in
air commerce. This regulation is within the scope of that authority
because it addresses an unsafe condition that is likely to exist or
develop on products identified in this rulemaking action.
Regulatory Findings
We have determined that this 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 the regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
0
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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2006-12-04 Viking Air Limited (Formerly Bombardier, Inc.): Amendment
39-14629. Docket No. FAA-2006-24966; Directorate Identifier 2006-NM-
049-AD.
Effective Date
(a) This AD becomes effective June 21, 2006.
Affected ADs
(b) None
Applicability
(c) This AD applies to Viking Air Limited Model DHC-7-1, DHC-7-
100, DHC-7-101, DHC-7-102, and DHC-7-103 airplanes, certificated in
any category; except airplanes having serial numbers 3 through 10
inclusive, 12 through 14 inclusive, and 16 through 27 inclusive.
Unsafe Condition
(d) This AD results from a report that the designed life limit
for the primary structure for the affected airplanes is 80,000 total
flight cycles. We are issuing this AD to prevent continued operation
of an airplane beyond its designed life limit for the primary
structure, which could result in reduced structural integrity of the
airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Airworthiness Limitations Revision
(f) Within 30 days after the effective date of this AD: Revise
the FAA-approved Airworthiness Limitations section (ALS) of the
Bombardier DHC-7 Dash 7 maintenance manual and the Dash 7 Series 150
maintenance manual to state the following (this may be done by
inserting a copy of this AD into the ALS). Thereafter, maintain the
airplane in accordance with the limitations specified in these
maintenance manual revisions:
``Do not operate the airplane beyond 80,000 total flight
cycles.''
(g) When the statement specified in paragraph (f) of this AD has
been included in the general revisions of the ALS, the general
revisions may be incorporated into the ALS and the copy of the AD
may be removed from the ALS.
(h) The airworthiness limitation specified in paragraph (f) of
this AD may be removed from the maintenance manuals specified in
paragraph (f) of this AD after the Manager, New York Aircraft
Certification Office (ACO), FAA, approves analysis that
substantiates continued safe operation beyond the designed life
limit of 80,000 total flight cycles.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, New York ACO, FAA, has the authority to
approve AMOCs for this AD, if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(j) Canadian airworthiness directive CF-2005-36, dated September
28, 2005, also addresses the subject of this AD.
Material Incorporated by Reference
(k) None.
Issued in Renton, Washington, on May 31, 2006.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-5119 Filed 6-5-06; 8:45 am]
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