Airworthiness Directives; MD Helicopters, Inc. Model MD-900 Helicopters, 12441-12445 [2010-5325]

Download as PDF Federal Register / Vol. 75, No. 50 / Tuesday, March 16, 2010 / Rules and Regulations FAA AD Differences Effective Date (a) This airworthiness directive (AD) becomes effective April 20, 2010. Affected ADs (b) None. Applicability (c) This AD applies to Thielert Aircraft Engines GmbH (TAE) models TAE 125–01 and TAE 125–02–99 reciprocating engines installed in, but not limited to, Cessna 172 and (Reims-built) F172 series (EASA STC No. EASA.A.S.01527); Piper PA–28 series (EASA STC No. EASA.A.S. 01632); APEX (Robin) DR 400 series (EASA STC No. A.S.01380); and Diamond Aircraft Industries Models DA40 and DA42 airplanes. Reason (d) As a consequence of occurrences and service experience, Thielert Aircraft Engines GmbH has introduced a new rail pressure control valve part number (P/N) 05–7320– E000702 and P/N 02–7320–04100R3 and has amended the Airworthiness Limitation Section (ALS) of the Operation & Maintenance Manual OM–02–02 to include a replacement of the rail pressure control valve. Failure of this part could result in inflight shutdowns of the engine(s). This AD results from mandatory continuing airworthiness information (MCAIs) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. We are issuing this AD to prevent engine in-flight shutdown, possibly resulting in reduced control of the aircraft. Actions and Compliance (e) Unless already done, do the following actions. emcdonald on DSK2BSOYB1PROD with RULES TAE 125–02–99 Reciprocating Engines (1) For TAE 125–02–99 reciprocating engines, within 100 flight hours after the effective date of this AD, replace the existing rail pressure control valve with a rail pressure control valve P/N 05–7320– E000702, and modify the Vrail plug to make it compatible with the replacement rail pressure control valve. (2) Guidance on the valve replacement and rail modification specified in paragraph (e)(1) of this AD can be found in Thielert Repair Manual RM–02–02, Chapter 73–10.08, and Chapter 39–40.08, respectively. TAE 125–01 Reciprocating Engines (3) For TAE 125–01 reciprocating engines, within 100 flight hours after the effective date of this AD, replace the existing rail pressure control valve with a rail pressure control valve, P/N 02–7320–04100R3. (4) Guidance on the valve replacement specified in paragraph (e)(3) of this AD can be found in Thielert Repair Manual RM–02– 01, Chapter 29.0. DEPARTMENT OF TRANSPORTATION (f) This AD differs from the Mandatory Continuing Airworthiness Information (MCAI) and/or service information as follows: (1) For the TAE 125–02–99 reciprocating engines, we reduced the initial compliance time from within 110 flight hours to within 100 flight hours after the effective date of this AD. (2) For the TAE 125–01 reciprocating engines, we changed initial compliance time from within the next 3 months to within 100 flight hours after the effective date of this AD. (3) The MCAIs instruct the operators to follow Thielert Maintenance Manual, Chapter 5, Airworthiness Limitations, for the repetitive replacement compliance time for the rail pressure control valve, which, in the manual, is 600 flight hours. We found it necessary to specify the repetitive replacement compliance time in this AD, of within every 600 flight hours. Alternative Methods of Compliance (AMOCs) (g) The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (h) Refer to MCAI European Aviation Safety Agency (EASA) AD 2008–0128, dated July 9, 2008, EASA AD 2008–0215, dated December 5, 2008, Thielert Service Bulletin No. TAE 125–1008 P1, Revision 1, dated September 29, 2008, and Thielert Repair Manual RM–02–02, for related information. Contact Thielert Aircraft Engines GmbH, Platanenstrasse 14 D–09350, Lichtenstein, Germany, telephone: +49–37204–696–0; fax: +49–37204–696–55; e-mail: info@centurionengines.com, for a copy of this service information. (i) Contact Tara Chaidez, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: tara.chaidez@faa.gov; telephone (781) 238–7773; fax (781) 238– 7199, for more information about this AD. Issued in Burlington, Massachusetts, on March 8, 2010. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2010–5548 Filed 3–15–10; 8:45 am] BILLING CODE 4910–13–P TAE 125–02–99 and TAE 125–01 Engines, Repetitive Replacements of Rail Pressure Control Valves (5) Thereafter, for affected TAE 125–02–99 and TAE 125–01 engines, replace the rail pressure control valve with the same P/N valve within every 600 flight hours. VerDate Nov<24>2008 15:08 Mar 15, 2010 Jkt 220001 PO 00000 Frm 00005 Fmt 4700 12441 Sfmt 4700 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0953; Directorate Identifier 2009–SW–45–AD; Amendment 39–16230; AD 2010–06–06] RIN 2120–AA64 Airworthiness Directives; MD Helicopters, Inc. Model MD–900 Helicopters AGENCY: Federal Aviation Administration, DOT. ACTION: Final rule. SUMMARY: This amendment supersedes an existing airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) model MD–900 helicopters that currently requires applying serial numbers to certain parts, increasing the life limit for various parts, maintaining a previously established life limit for a certain vertical stabilizer control system (VSCS) bellcrank assembly and bellcrank arm, and correcting the part number for the VSCS bellcrank arm. This amendment requires the same actions as the existing AD, except it reduces the life limit of the swashplate spherical slider bearing (slider bearing). It further corrects what was described as a ‘‘bellcrank arm’’ life limit in the current AD and correctly describes it as another ‘‘bellcrank assembly’’ life limit. This amendment is prompted by two reports of cracks in the slider bearing that occurred well before the previously increased retirement life of 2,030 hours time-in-service (TIS) was reached. The actions specified by this AD are intended to establish appropriate life limits for various parts, and to prevent fatigue failure of those parts and subsequent loss of control of the helicopter. DATES: Effective April 20, 2010. 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, E:\FR\FM\16MRR1.SGM 16MRR1 12442 Federal Register / Vol. 75, No. 50 / Tuesday, March 16, 2010 / Rules and Regulations 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 by superseding AD 99–16–13, Amendment 39–11248 (64 FR 42824, August 6, 1999), Docket No. 98–SW–42–AD, for the MDHI Model MD–900 helicopters was published in the Federal Register on October 22, 2009 (74 FR 54495). The action proposed to decrease the life limit of the slider bearing from 2,030 hours TIS to 700 hours time-in-service (TIS). Additionally, changing the nomenclature for part number 900F2341712–101 from bellcrank arm to bellcrank assembly was proposed. The action also proposed to retain the requirements of the existing AD to apply serial numbers to various parts, and to retain the life limits of various other parts. Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or the FAA’s determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule as proposed. The FAA estimates that this AD will affect 27 helicopters of U.S. registry, and that it will take approximately 2.5 work hours per helicopter to accomplish the serialization of the affected parts at an average labor rate of $85 per work hour. Additionally, it is estimated that 8 of those aircraft will require replacement of the slider bearing, which will require approximately 7 work hours to accomplish at an average labor rate of $85 per work hour. Required parts will cost approximately $11,080 per helicopter for the slider bearing. Based on these figures, we estimate the total cost impact of the AD on U.S. operators to be $99,137. emcdonald on DSK2BSOYB1PROD with RULES 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: VerDate Nov<24>2008 15:08 Mar 15, 2010 Jkt 220001 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, 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: ■ PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by removing Amendment 39–11248 (64 FR 42824, August 6, 1999), and by adding a new airworthiness directive (AD), Amendment 39–16230, to read as follows: ■ PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 2010–06–06 MD Helicopters, Inc.: Amendment 39–16230. Docket No. FAA–2009–0953; Directorate Identifier 2009–SW–45–AD. Supersedes AD 99– 16–13, Amendment 39–11248, Docket No. 98–SW–42–AD. Applicability: MD–900 helicopters, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To establish appropriate life limits for various parts, and to prevent fatigue failure of those parts and subsequent loss of control of the helicopter, accomplish the following: (a) Remove from service as follows: (1) The nonrotating swashplate assembly, part number (P/N) 900C2010192–105, –107, –109, or –111, on or before 1,800 hours timein-service (TIS). (2) The collective drive link assembly, P/N 900C2010207–101, on or before 3,307 hours TIS. (3) The swashplate spherical slider bearing, P/N 900C3010042–103, on or before 700 hours TIS. (4) The vertical stabilizer control system (VSCS) bellcrank assembly, P/N 900FP341712–103, and bellcrank assembly, P/N 900F2341712–101, on or before 2,700 hours TIS. (b) Within 100 hours TIS: (1) For Model MD–900 helicopters with serial numbers (S/N) 900–00002 through 900–00012, apply the appropriate S/N to the mid-forward truss assembly, P/N 900F2401200–102, and the forward and aft deck-fitting assemblies, P/N 900F2401500– 103 and P/N 900F2401600–103. (2) For Model MD–900 helicopters with S/N 900–00002 through 900–00048, apply S/N to the left and right VSCS bellcrank assemblies, P/N 900F2341712–101 and P/N 900FP341712–103, and the mid-aft truss strut assembly, P/N 900F2401300–103. (3) Apply the S/N, as specified in paragraphs (b)(1) and (b)(2) of this AD, adjacent to the existing P/N, as listed in Appendix A of this AD, using permanent ink or paint. When dry, apply a clear coat over the S/N. (c) This AD revises the Airworthiness Limitations Section of the MD–900 Maintenance Manual by increasing the life limits for certain parts and reducing the life limit of the slider bearing. Note: The Airworthiness Limitations Section of the MD–900 Rotorcraft Maintenance Manual, Reissue 1, Revision 25, dated April 16, 2006, and MD Helicopters Service Bulletin SB900–096, dated February 28, 2005, pertain to the subject of this AD. (d) 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, for information about previously approved alternative methods of compliance. BILLING CODE 4910–13–P E:\FR\FM\16MRR1.SGM 16MRR1 VerDate Nov<24>2008 15:08 Mar 15, 2010 Jkt 220001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4725 E:\FR\FM\16MRR1.SGM 16MRR1 12443 ER16MR10.000</GPH> emcdonald on DSK2BSOYB1PROD with RULES Federal Register / Vol. 75, No. 50 / Tuesday, March 16, 2010 / Rules and Regulations VerDate Nov<24>2008 Federal Register / Vol. 75, No. 50 / Tuesday, March 16, 2010 / Rules and Regulations 15:08 Mar 15, 2010 Jkt 220001 PO 00000 Frm 00008 Fmt 4700 Sfmt 9990 E:\FR\FM\16MRR1.SGM 16MRR1 ER16MR10.001</GPH> emcdonald on DSK2BSOYB1PROD with RULES 12444 Federal Register / Vol. 75, No. 50 / Tuesday, March 16, 2010 / Rules and Regulations (e) This amendment becomes effective on April 20, 2010. Issued in Fort Worth, Texas, on February 18, 2010. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2010–5325 Filed 3–15–10; 8:45 am] BILLING CODE 4910–13–C DEPARTMENT OF HOMELAND SECURITY U.S. Customs and Border Protection U.S. Immigration and Customs Enforcement DEPARTMENT OF THE TREASURY 19 CFR Chapters I and IV [CBP Dec. 10–03] Name Change of Two DHS Components U.S. Customs and Border Protection, DHS; U.S. Immigration and Customs Enforcement, DHS; Department of the Treasury. ACTION: Final rule. AGENCY: On March 31, 2007, the name of the Bureau of Customs and Border Protection changed to U.S. Customs and Border Protection (CBP) and the name of the Bureau of Immigration and Customs Enforcement changed to U.S. Immigration and Customs Enforcement (ICE). This final rule revises two chapter headings in title 19 of the Code of Federal Regulations to reflect the name changes for those two Department of Homeland Security (DHS) components. DATES: Effective Date: March 16, 2010. FOR FURTHER INFORMATION CONTACT: For CBP: Harold Singer, Director, Regulations and Disclosure Law Division, Office of International Trade, U.S. Customs and Border Protection, (202) 325–0101. For ICE: Jason J. Johnsen, Writer/Editor, Office of Policy, U.S. Immigration and Customs Enforcement, (202) 732–4245. SUPPLEMENTARY INFORMATION: SUMMARY: Customs Service was renamed as the ‘‘Bureau of Customs and Border Protection’’ pursuant to section 1502 of the HSA. Section 442 of the HSA (6 U.S.C. 252) established the ‘‘Bureau of Border Security.’’ Under section 1502 of the HSA, the Bureau of Border Security was renamed as the ‘‘Bureau of Immigration and Customs Enforcement,’’ effective March 1, 2003. The President’s ‘‘Reorganization Plan Modification for the Department of Homeland Security,’’ dated January 30, 2003, memorializes these name changes. On January 18, 2007, DHS notified Congress that it was changing the name of the Bureau of Customs and Border Protection to ‘‘U.S. Customs and Border Protection (CBP)’’ and the name of the Bureau of Immigration and Customs Enforcement to ‘‘U.S. Immigration and Customs Enforcement (ICE).’’ Pursuant to section 872(a)(2) of the HSA (6 U.S.C. 452(a)(2), notice of the name change was provided to Congress no later than 60 days before the change could become effective. On April 23, 2007, a notice was published in the Federal Register to inform the public that DHS had changed the names of the two components effective March 31, 2007. 72 FR 20131. This document revises the headings of chapters I and IV of title 19 of the Code of Federal Regulations (19 CFR) to reflect the agency name changes as set forth in the Federal Register notice of April 23, 2007. Inapplicability of Prior Public Notice and Delayed Effective Date Requirements This regulation involves matters relating to agency management and involves a technical change regarding the name of the two DHS components. For this reason, pursuant to 5 U.S.C. 553(a)(2), prior notice and comment is not required. Because this is not a substantive rule, publication and service of the rule thirty days before its effective date, pursuant to 5 U.S.C. 553(d), is likewise not required. 12445 name change for CBP and ICE, the headings of chapters I and IV of title 19 of the Code of Federal Regulations are amended as set forth below: ■ 1. Revise the chapter I heading to title 19 to read as follows. Chapter I—U.S. Customs and Border Protection, Department of Homeland Security; Department of the Treasury 2. Revise the chapter IV heading to title 19 to read as follows. ■ Chapter IV—U.S. Immigration and Customs Enforcement; Department of Homeland Security Dated: March 10, 2010. Janet Napolitano, Secretary, Department of Homeland Security. Timothy E. Skud, Deputy Assistant Secretary, Tax, Tariff, and Trade Policy, Department of the Treasury. [FR Doc. 2010–5639 Filed 3–15–10; 8:45 am] BILLING CODE 9111–14–P POSTAL REGULATORY COMMISSION 39 CFR Part 3020 [Docket Nos. MC2010–18, CP2010–21 and CP2010–22; Order No. 414] New Postal Product Postal Regulatory Commission. Final rule. AGENCY: ACTION: SUMMARY: The Commission is adding International Business Reply Service Competitive Contract 2 to the Competitive Product List. This action is consistent with a postal reform law. Republication of the Market Dominant and Competitive Product Lists is also consistent with new statutory provisions. DATES: Effective March 16, 2010 and is applicable beginning February 26, 2010. FOR FURTHER INFORMATION CONTACT: Stephen L. Sharfman, General Counsel, 202–789–6820 or stephen.sharfman@prc.gov. emcdonald on DSK2BSOYB1PROD with RULES Background On November 25, 2002, the President signed the Homeland Security Act of 2002, 6 U.S.C. 101 et seq., Public Law 107–296, (the ‘‘HSA’’), establishing the Department of Homeland Security (DHS). Pursuant to section 403(1) of the HSA (6 U.S.C. 203(1)), the U.S. Customs Service was transferred from the Department of the Treasury to DHS effective March 1, 2003. In addition, the The Regulatory Flexibility Act and Executive Order 12866 Because no notice of proposed rulemaking is required, the provisions of the Regulatory Flexibility Act (5 U.S.C. 601 et seq.) do not apply. Further, this amendment does not meet the criteria for a ‘‘significant regulatory action’’ for purposes of Executive Order 12866. Amendments to the Regulations I. Introduction For the reasons set forth above in the preamble, under the authority of 6 U.S.C. 452, and the April 23, 2007, DHS Federal Register notice announcing the The Postal Service seeks to add a new product identified as International Business Reply Service Competitive Contract 2 to the Competitive Product VerDate Nov<24>2008 15:08 Mar 15, 2010 Jkt 220001 ■ PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 Regulatory History, 74 FR 49823 (September 29, 2009). SUPPLEMENTARY INFORMATION: Table of Contents I. Introduction II. Background III. Comments IV. Commission Analysis V. Ordering Paragraphs E:\FR\FM\16MRR1.SGM 16MRR1

Agencies

[Federal Register Volume 75, Number 50 (Tuesday, March 16, 2010)]
[Rules and Regulations]
[Pages 12441-12445]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-5325]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0953; Directorate Identifier 2009-SW-45-AD; 
Amendment 39-16230; AD 2010-06-06]
RIN 2120-AA64


Airworthiness Directives; MD Helicopters, Inc. Model MD-900 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) for MD Helicopters, Inc. (MDHI) model MD-900 helicopters that 
currently requires applying serial numbers to certain parts, increasing 
the life limit for various parts, maintaining a previously established 
life limit for a certain vertical stabilizer control system (VSCS) 
bellcrank assembly and bellcrank arm, and correcting the part number 
for the VSCS bellcrank arm. This amendment requires the same actions as 
the existing AD, except it reduces the life limit of the swashplate 
spherical slider bearing (slider bearing). It further corrects what was 
described as a ``bellcrank arm'' life limit in the current AD and 
correctly describes it as another ``bellcrank assembly'' life limit. 
This amendment is prompted by two reports of cracks in the slider 
bearing that occurred well before the previously increased retirement 
life of 2,030 hours time-in-service (TIS) was reached. The actions 
specified by this AD are intended to establish appropriate life limits 
for various parts, and to prevent fatigue failure of those parts and 
subsequent loss of control of the helicopter.

DATES: Effective April 20, 2010.

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,

[[Page 12442]]

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 by 
superseding AD 99-16-13, Amendment 39-11248 (64 FR 42824, August 6, 
1999), Docket No. 98-SW-42-AD, for the MDHI Model MD-900 helicopters 
was published in the Federal Register on October 22, 2009 (74 FR 
54495). The action proposed to decrease the life limit of the slider 
bearing from 2,030 hours TIS to 700 hours time-in-service (TIS). 
Additionally, changing the nomenclature for part number 900F2341712-101 
from bellcrank arm to bellcrank assembly was proposed. The action also 
proposed to retain the requirements of the existing AD to apply serial 
numbers to various parts, and to retain the life limits of various 
other parts.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.
    The FAA estimates that this AD will affect 27 helicopters of U.S. 
registry, and that it will take approximately 2.5 work hours per 
helicopter to accomplish the serialization of the affected parts at an 
average labor rate of $85 per work hour. Additionally, it is estimated 
that 8 of those aircraft will require replacement of the slider 
bearing, which will require approximately 7 work hours to accomplish at 
an average labor rate of $85 per work hour. Required parts will cost 
approximately $11,080 per helicopter for the slider bearing. Based on 
these figures, we estimate the total cost impact of the AD on U.S. 
operators to be $99,137.

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, 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 removing Amendment 39-11248 (64 FR 
42824, August 6, 1999), and by adding a new airworthiness directive 
(AD), Amendment 39-16230, to read as follows:

2010-06-06 MD Helicopters, Inc.: Amendment 39-16230. Docket No. FAA-
2009-0953; Directorate Identifier 2009-SW-45-AD. Supersedes AD 99-
16-13, Amendment 39-11248, Docket No. 98-SW-42-AD.

    Applicability: MD-900 helicopters, certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To establish appropriate life limits for various parts, and to 
prevent fatigue failure of those parts and subsequent loss of 
control of the helicopter, accomplish the following:
    (a) Remove from service as follows:
    (1) The nonrotating swashplate assembly, part number (P/N) 
900C2010192-105, -107, -109, or -111, on or before 1,800 hours time-
in-service (TIS).
    (2) The collective drive link assembly, P/N 900C2010207-101, on 
or before 3,307 hours TIS.
    (3) The swashplate spherical slider bearing, P/N 900C3010042-
103, on or before 700 hours TIS.
    (4) The vertical stabilizer control system (VSCS) bellcrank 
assembly, P/N 900FP341712-103, and bellcrank assembly, P/N 
900F2341712-101, on or before 2,700 hours TIS.
    (b) Within 100 hours TIS:
    (1) For Model MD-900 helicopters with serial numbers (S/N) 900-
00002 through 900-00012, apply the appropriate S/N to the mid-
forward truss assembly, P/N 900F2401200-102, and the forward and aft 
deck-fitting assemblies, P/N 900F2401500-103 and P/N 900F2401600-
103.
    (2) For Model MD-900 helicopters with S/N 900-00002 through 900-
00048, apply S/N to the left and right VSCS bellcrank assemblies, P/
N 900F2341712-101 and P/N 900FP341712-103, and the mid-aft truss 
strut assembly, P/N 900F2401300-103.
    (3) Apply the S/N, as specified in paragraphs (b)(1) and (b)(2) 
of this AD, adjacent to the existing P/N, as listed in Appendix A of 
this AD, using permanent ink or paint. When dry, apply a clear coat 
over the S/N.
    (c) This AD revises the Airworthiness Limitations Section of the 
MD-900 Maintenance Manual by increasing the life limits for certain 
parts and reducing the life limit of the slider bearing.

    Note: The Airworthiness Limitations Section of the MD-900 
Rotorcraft Maintenance Manual, Reissue 1, Revision 25, dated April 
16, 2006, and MD Helicopters Service Bulletin SB900-096, dated 
February 28, 2005, pertain to the subject of this AD.

    (d) 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, 
for information about previously approved alternative methods of 
compliance.
BILLING CODE 4910-13-P

[[Page 12443]]

[GRAPHIC] [TIFF OMITTED] TR16MR10.000


[[Page 12444]]


[GRAPHIC] [TIFF OMITTED] TR16MR10.001


[[Page 12445]]


    (e) This amendment becomes effective on April 20, 2010.

    Issued in Fort Worth, Texas, on February 18, 2010.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-5325 Filed 3-15-10; 8:45 am]
BILLING CODE 4910-13-C
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.