Airworthiness Directives; MD Helicopters, Inc. Model MD900 Series Helicopters, 22787-22789 [E8-8638]

Download as PDF Federal Register / Vol. 73, No. 82 / Monday, April 28, 2008 / Rules and Regulations to be authorized by the ESP, LWA, construction permit, or combined license in light of the preconstruction impacts. 2. On page 57433, third column, the last paragraph is revised to read as follows: Section 51.4 is revised by adding a new definition of ‘‘construction,’’ which is identical to the definition of construction in the revised § 50.10. This makes applicable throughout part 51 the definition of construction in § 50.10. 3. On page 57434, in the first column, the first paragraph is removed. 4. On page 57434, in the first column, the paragraph under § 51.45 is corrected to read as follows: Paragraph (c) is revised by adding a new requirement requiring environmental reports for ESPs, LWAs, construction permits, and combined licenses to include a description of impacts of the applicant’s preconstruction activities at the proposed site (i.e., the activities listed in paragraphs (2)(i) through (2)(x) in the definition of ‘‘construction’’ contained in § 51.4), that are necessary to support the construction and operation of the facility which is the subject of the ESP, LWA, construction permit, or combined license application, and an analysis of the cumulative impacts of the activities to be authorized by the ESP, LWA, construction permit, or combined license in light of the preconstruction impacts. List of Subjects in 10 CFR Part 51 Administrative practice and procedure, Environmental impact statement, Nuclear materials, Nuclear power plants and reactors, Reporting and recordkeeping requirements. For the reasons set out in the preamble and under the authority of the Atomic Energy Act of 1954, as amended; the Energy Reorganization Act of 1974, as amended; and 5 U.S.C. 552 and 553, the NRC is adopting the following amendment to 10 CFR part 51. I PART 51—ENVIRONMENTAL PROTECTION REGULATIONS FOR DOMESTIC LICENSING AND RELATED REGULATORY FUNCTIONS 1. The authority citation for part 51 continues to read as follows: hsrobinson on PROD1PC76 with RULES I 16:07 Apr 25, 2008 Jkt 214001 2. In § 51.45, paragraph (c), the second complete sentence is corrected to read as follows: I § 51.45 Environmental report. * * * * * (c) * * * An environmental report prepared at the early site permit stage under § 51.50(b), limited work authorization stage under § 51.49, construction permit stage under § 51.50(a), or combined license stage under § 51.50(c) must include a description of impacts of the preconstruction activities performed by the applicant at the proposed site (i.e., those activities listed in paragraphs (2)(i) through (2)(x) in the definition of ‘‘construction’’ contained in § 51.4), necessary to support the construction and operation of the facility which is the subject of the early site permit, limited work authorization, construction permit, or combined license application. * * * * * * * * Dated at Rockville, Maryland, this 18th day of April 2008. For the Nuclear Regulatory Commission. Annette L. Vietti-Cook, Secretary of the Commission. [FR Doc. E8–8890 Filed 4–25–08; 8:45 am] BILLING CODE 7590–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25983; Directorate Identifier 2006–SW–11–AD; Amendment 39– 15463; AD 2008–08–11] RIN 2120–AA64 Authority: Sec. 161, 68 Stat. 948, as amended, sec. 1701, 106 Stat. 2951, 2952, 2953, (42 U.S.C. 2201, 2297f); secs. 201, as amended, 202, 88 Stat. 1242, as amended, 1244 (42 U.S.C. 5841, 5842); sec. 1704, 112 Stat. 2750 (44 U.S.C. 3504 note). Subpart A also issued under National Environmental Policy Act of 1969, secs. 102, 104, 105, 83 Stat. 853–854, as amended (42 U.S.C. 4332, VerDate Aug<31>2005 4334, 4335); and Pub. L. 95–604, Title II, 92 Stat. 3033–3041; and sec. 193, Pub. L. 101– 575, 104 Stat. 2835 (42 U.S.C. 2243). Sections 51.20, 51.30, 51.60, 51.80. and 51.97 also issued under secs. 135, 141, Pub. L. 97–425, 96 Stat. 2232, 2241, and sec. 148, Pub. L. 100–203, 101 Stat. 1330–223 (42 U.S.C. 10155, 10161, 10168). Section 51.22 also issued under sec. 274, 73 Stat. 688, as amended by 92 Stat. 3036–3038 (42 U.S.C. 2021) and under Nuclear Waste Policy Act of 1982, sec. 121, 96 Stat. 2228 (42 U.S.C. 10141). Sections 51.43, 51.67, and 51.109 also issued under Nuclear Waste Policy Act of 1982, sec. 114(f), 96 Stat. 2216, as amended (42 U.S.C. 10134(f)). Airworthiness Directives; MD Helicopters, Inc. Model MD900 Series Helicopters Federal Aviation Administration, DOT. ACTION: Final rule. AGENCY: PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 22787 SUMMARY: This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model MD900 series helicopters that requires modifying the pilot and co-pilot dualcontrol directional pedal assemblies, or the pilot single-control directional pedal assembly (directional control pedal assembly). This amendment is prompted by an accident which has been attributed to loss of directional control due to failure of the welds in the directional control pedal assembly. The actions specified by this AD are intended to prevent fatigue cracking in the welds that connect the directional control pedal to the pedal shaft, resulting in loss of directional control and subsequent loss of control of the helicopter. Effective June 2, 2008. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of June 2, 2008. DATES: You may get the service information identified in this AD from MD Helicopters, Inc., Attn: Customer Support Division, 4555 E. McDowell Rd., Mail Stop M615, Mesa, Arizona 85215–9734, telephone 1–800–388– 3378, fax 480–346–6813, or on the Web at https://www.mdhelicopters.com. Examining the Docket: You may examine the docket that contains this AD, any comments, and other information on the Internet at https:// www.regulations.gov or at the Docket Operations office, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. ADDRESSES: FOR FURTHER INFORMATION CONTACT: Roger Durbin, Aviation Safety Engineer, FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960 Paramount Blvd., Lakewood, California 90712, telephone (562) 627–5233, fax (562) 627–5210. SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to include an AD for the specified model helicopters was published in the Federal Register on October 17, 2006 (71 FR 60927). That action proposed to require, for MDHI Model MD900 series helicopters, serial numbers (S/N) 900– 00008 through 900–00111, 900–00113, and 900–00114, modifying the directional control pedal assembly, part number (P/N) 900C1012007–107, –109, –111, –113, or 900C6012007–111 (pilot dual control); or P/N 900C1012207–105, –107, –109, –111, or –113 (co-pilot dual control); or P/N 900C1010007–107, –109, –111, –113, or 900C6010007–111 E:\FR\FM\28APR1.SGM 28APR1 22788 Federal Register / Vol. 73, No. 82 / Monday, April 28, 2008 / Rules and Regulations hsrobinson on PROD1PC76 with RULES (pilot single control), by removing the existing pedals, removing the welded pedal support plate from the pedal shafts, and installing a directional control pedal modification kit, P/N SBK–010. Ink stamping the P/N, 90005340111–101, on the pedal shaft of each modified directional control pedal assembly using permanent ink was also proposed. MDHI has issued Service Bulletin SB900–100, dated April 5, 2006, which describes procedures for modifying the directional control pedal assembly. Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received. The one commenter, the Modification and Replacement Parts Association, ‘‘does not object to the TC holder provided modification kits provided at no cost to operators’’ and states that ‘‘Such action removes any incentive for the development of alternative parts under 14 CFR 21.303.’’ They also note that the cost impact stated in the AD is $61,650 per helicopter, but should correctly be stated as $61,650 for the entire U.S. fleet of MDHI MD900 helicopters. The FAA concurs and has corrected that error in this AD. After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule with the change described previously. The FAA has determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. The FAA estimates that this AD will affect 30 helicopters of U.S. registry, and the required actions will take approximately 8 work hours for helicopters with single pilot controls installed, or 16 work hours for helicopters with dual pilot and co-pilot controls installed, at an average labor rate of $80 per work hour. Required parts will cost approximately $775 for helicopters with dual pilot and co-pilot controls installed. Based on these figures, we estimate the total cost impact of the AD on U.S. operators to be $61,650 for the entire fleet, or $2,055 per helicopter, assuming that dual pilot and co-pilot controls are installed on the entire fleet and there is no warranty coverage. 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 VerDate Aug<31>2005 16:07 Apr 25, 2008 Jkt 214001 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 an economic evaluation of the estimated costs to comply with this AD. See the AD docket to examine the economic evaluation. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to 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. Section 39.13 is amended by adding a new airworthiness directive to read as follows: I PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 2008–08–11 MD Helicopters, Inc.: Amendment 39–15463. Docket No. FAA–2006–25983; Directorate Identifier 2006–SW–11–AD. Applicability Model MD900 series helicopters, serial numbers (S/N) 900–00008 through 900– 00111, 900–00113, and 900–00114, certificated in any category. Compliance Required within 90 days after the effective date of this AD, unless accomplished previously. To prevent fatigue cracking in the welds which connect the pilot and co-pilot dualcontrol, or pilot single-control directional control pedal (directional control pedal) to the pedal shaft, resulting in loss of directional control and subsequent loss of control of the helicopter, accomplish the following: (a) Modify each directional control pedal assembly, part number (P/N) 900C1012007– 107, –109, –111, –113, or 900C6012007–111 (pilot dual control); or P/N 900C1012207– 105, –107, –109, –111, or –113 (co-pilot dual control); or P/N 900C1010007–107, –109, –111, –113, or 900C6010007–111 (pilot single control), by removing the existing pedals, removing the welded pedal support plate from the pedal shafts, and installing a directional control pedal modification kit, P/N SBK–010, in accordance with part 2, Accomplishment Instructions, in MD Helicopters Service Bulletin SB900–100, dated April 5, 2006. One modification kit is required to be installed on helicopters with single controls and two modification kits are required to be installed on helicopters with dual controls. (b) Using a permanent ink, ink stamp the P/N, 90005340111–101, on the pedal shaft of each modified directional control pedal assembly. (c) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Los Angeles Aircraft Certification Office, FAA, ATTN: Roger Durbin, Airframe Branch, 3960 Paramount Blvd., Lakewood, California 90712, telephone (562) 627–5233, fax (562) 627–5210, for information about previously approved alternative methods of compliance. (d) The modification shall be done in accordance with the specified portions of MD Helicopters Service Bulletin SB900–100, dated April 5, 2006. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from MD Helicopters, Inc., Attn: Customer Support Division, 4555 E. McDowell Rd., Mail Stop M615, Mesa, Arizona 85215–9734, telephone 1–800–388– 3378, fax 480–346–6813. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas, or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal_register/ E:\FR\FM\28APR1.SGM 28APR1 Federal Register / Vol. 73, No. 82 / Monday, April 28, 2008 / Rules and Regulations code_of_federal_regulations/ ibr_locations.html. (e) This amendment becomes effective on June 2, 2008. Issued in Fort Worth, Texas, on April 3, 2008. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E8–8638 Filed 4–25–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–29248; Directorate Identifier 2007–NM–155–AD; Amendment 39–15487; AD 2008–09–06] RIN 2120–AA64 Airworthiness Directives; Saab Model SAAB-Fairchild SF340A (SAAB/ SF340A) and SAAB 340B Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, * * * Special Federal Aviation Regulation 88 (SFAR88) * * * required a safety review of the aircraft Fuel Tank System * * *. * * * * * hsrobinson on PROD1PC76 with RULES Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an ‘unsafe condition’ * * *. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers’ requirements. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective June 2, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 2, 2008. ADDRESSES: You may examine the AD docket on the Internet at https:// VerDate Aug<31>2005 16:07 Apr 25, 2008 Jkt 214001 www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Mike Borfitz, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2677; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That supplemental NPRM was published in the Federal Register on March 6, 2008 (73 FR 12034). That supplemental NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, the FAA published Special Federal Aviation Regulation 88 (SFAR 88) in June 2001. SFAR 88 required a safety review of the aircraft Fuel Tank System to determine that the design meets the requirements of FAR (Federal Aviation Regulation) § 25.901 and § 25.981(a) and (b). A similar regulation has been recommended by the JAA (Joint Aviation Authorities) to the European National Aviation Authorities in JAA letter 04/00/02/ 07/03–L024 of 3 February 2003. The review was requested to be mandated by NAA’s (National Aviation Authorities) using JAR (Joint Aviation Regulation) § 25.901(c), § 25.1309. In August 2005 EASA published a policy statement on the process for developing instructions for maintenance and inspection of Fuel Tank System ignition source prevention (EASA D 2005/CPRO, www.easa.eu.int/home/ cert_policy_statements_en.html) that also included the EASA expectations with regard to compliance times of the corrective actions on the unsafe and the not unsafe part of the harmonised design review results. On a global scale the TC (type certificate) holders committed themselves to the EASA published compliance dates (see EASA policy statement). The EASA policy statement has been revised in March 2006: the date of 31–12–2005 for the unsafe related actions has now been set at 01–07–2006. Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an ‘unsafe condition’ as defined in FAA’s memo 2003–112–15 ‘SFAR 88—Mandatory Action Decision Criteria’. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers’ requirements. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 22789 This EASA Airworthiness Directive mandates the Fuel System Airworthiness Limitations (comprising maintenance/ inspection tasks and Critical Design Configuration Control Limitations (CDCCL)) for the type of aircraft, that resulted from the design reviews and the JAA recommendation and EASA policy statement mentioned above. The corrective action is revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect about 144 products of U.S. registry. We also estimate that it will take about 1 work-hour per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $11,520, or $80 per product. 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. E:\FR\FM\28APR1.SGM 28APR1

Agencies

[Federal Register Volume 73, Number 82 (Monday, April 28, 2008)]
[Rules and Regulations]
[Pages 22787-22789]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-8638]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25983; Directorate Identifier 2006-SW-11-AD; 
Amendment 39-15463; AD 2008-08-11]
RIN 2120-AA64


Airworthiness Directives; MD Helicopters, Inc. Model MD900 Series 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
MD Helicopters, Inc. (MDHI) Model MD900 series helicopters that 
requires modifying the pilot and co-pilot dual-control directional 
pedal assemblies, or the pilot single-control directional pedal 
assembly (directional control pedal assembly). This amendment is 
prompted by an accident which has been attributed to loss of 
directional control due to failure of the welds in the directional 
control pedal assembly. The actions specified by this AD are intended 
to prevent fatigue cracking in the welds that connect the directional 
control pedal to the pedal shaft, resulting in loss of directional 
control and subsequent loss of control of the helicopter.

DATES: Effective June 2, 2008.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 2, 2008.

ADDRESSES: You may get the service information identified in this AD 
from MD Helicopters, Inc., Attn: Customer Support Division, 4555 E. 
McDowell Rd., Mail Stop M615, Mesa, Arizona 85215-9734, telephone 1-
800-388-3378, fax 480-346-6813, or on the Web at https://
www.mdhelicopters.com.
    Examining the Docket: You may examine the docket that contains this 
AD, any comments, and other information on the Internet at https://
www.regulations.gov or at the Docket Operations office, West Building 
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, 
DC.

FOR FURTHER INFORMATION CONTACT: Roger Durbin, Aviation Safety 
Engineer, FAA, Los Angeles Aircraft Certification Office, Airframe 
Branch, 3960 Paramount Blvd., Lakewood, California 90712, telephone 
(562) 627-5233, fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to 
include an AD for the specified model helicopters was published in the 
Federal Register on October 17, 2006 (71 FR 60927). That action 
proposed to require, for MDHI Model MD900 series helicopters, serial 
numbers (S/N) 900-00008 through 900-00111, 900-00113, and 900-00114, 
modifying the directional control pedal assembly, part number (P/N) 
900C1012007-107, -109, -111, -113, or 900C6012007-111 (pilot dual 
control); or P/N 900C1012207-105, -107, -109, -111, or -113 (co-pilot 
dual control); or P/N 900C1010007-107, -109, -111, -113, or 
900C6010007-111

[[Page 22788]]

(pilot single control), by removing the existing pedals, removing the 
welded pedal support plate from the pedal shafts, and installing a 
directional control pedal modification kit, P/N SBK-010. Ink stamping 
the P/N, 90005340111-101, on the pedal shaft of each modified 
directional control pedal assembly using permanent ink was also 
proposed.
    MDHI has issued Service Bulletin SB900-100, dated April 5, 2006, 
which describes procedures for modifying the directional control pedal 
assembly.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    The one commenter, the Modification and Replacement Parts 
Association, ``does not object to the TC holder provided modification 
kits provided at no cost to operators'' and states that ``Such action 
removes any incentive for the development of alternative parts under 14 
CFR 21.303.'' They also note that the cost impact stated in the AD is 
$61,650 per helicopter, but should correctly be stated as $61,650 for 
the entire U.S. fleet of MDHI MD900 helicopters. The FAA concurs and 
has corrected that error in this AD.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change described 
previously. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.
    The FAA estimates that this AD will affect 30 helicopters of U.S. 
registry, and the required actions will take approximately 8 work hours 
for helicopters with single pilot controls installed, or 16 work hours 
for helicopters with dual pilot and co-pilot controls installed, at an 
average labor rate of $80 per work hour. Required parts will cost 
approximately $775 for helicopters with dual pilot and co-pilot 
controls installed. Based on these figures, we estimate the total cost 
impact of the AD on U.S. operators to be $61,650 for the entire fleet, 
or $2,055 per helicopter, assuming that dual pilot and co-pilot 
controls are installed on the entire fleet and there is no warranty 
coverage.

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 an economic evaluation of the estimated costs to comply 
with this AD. See the AD docket to examine the economic evaluation.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to 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. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2008-08-11 MD Helicopters, Inc.: Amendment 39-15463. Docket No. FAA-
2006-25983; Directorate Identifier 2006-SW-11-AD.

Applicability

    Model MD900 series helicopters, serial numbers (S/N) 900-00008 
through 900-00111, 900-00113, and 900-00114, certificated in any 
category.

Compliance

    Required within 90 days after the effective date of this AD, 
unless accomplished previously.
    To prevent fatigue cracking in the welds which connect the pilot 
and co-pilot dual-control, or pilot single-control directional 
control pedal (directional control pedal) to the pedal shaft, 
resulting in loss of directional control and subsequent loss of 
control of the helicopter, accomplish the following:
    (a) Modify each directional control pedal assembly, part number 
(P/N) 900C1012007-107, -109, -111, -113, or 900C6012007-111 (pilot 
dual control); or P/N 900C1012207-105, -107, -109, -111, or -113 
(co-pilot dual control); or P/N 900C1010007-107, -109, -111, -113, 
or 900C6010007-111 (pilot single control), by removing the existing 
pedals, removing the welded pedal support plate from the pedal 
shafts, and installing a directional control pedal modification kit, 
P/N SBK-010, in accordance with part 2, Accomplishment Instructions, 
in MD Helicopters Service Bulletin SB900-100, dated April 5, 2006. 
One modification kit is required to be installed on helicopters with 
single controls and two modification kits are required to be 
installed on helicopters with dual controls.
    (b) Using a permanent ink, ink stamp the P/N, 90005340111-101, 
on the pedal shaft of each modified directional control pedal 
assembly.
    (c) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Los Angeles Aircraft Certification Office, FAA, 
ATTN: Roger Durbin, Airframe Branch, 3960 Paramount Blvd., Lakewood, 
California 90712, telephone (562) 627-5233, fax (562) 627-5210, for 
information about previously approved alternative methods of 
compliance.
    (d) The modification shall be done in accordance with the 
specified portions of MD Helicopters Service Bulletin SB900-100, 
dated April 5, 2006. The Director of the Federal Register approved 
this incorporation by reference in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51. Copies may be obtained from MD Helicopters, Inc., 
Attn: Customer Support Division, 4555 E. McDowell Rd., Mail Stop 
M615, Mesa, Arizona 85215-9734, telephone 1-800-388-3378, fax 480-
346-6813. Copies may be inspected at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas, or at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_
register/

[[Page 22789]]

code--of--federal--regulations/ibr--locations.html.
    (e) This amendment becomes effective on June 2, 2008.

    Issued in Fort Worth, Texas, on April 3, 2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-8638 Filed 4-25-08; 8:45 am]
BILLING CODE 4910-13-P

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