Airworthiness Directives; Viking Air Limited Model DHC-7 Airplanes, 32434-32436 [06-5119]

Download as PDF 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 PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 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 http:// dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://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 Sfmt 4700 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 http:// 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 http://dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at http://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 E:\FR\FM\06JNR1.SGM 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. PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 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 http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
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 http://
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 
http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://
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]
BILLING CODE 4910-13-P