Airworthiness Directives; MD Helicopters, Inc. Model 600N Helicopters, 13096-13098 [E8-4489]

Download as PDF 13096 Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations TABLE 2.—TERMINATING ACTIONS—Continued In accordance with the Accomplishment Instructions of Airbus Service Bulletin— Inspect— (2) The elevator servo controls, P/N SC4800–10 and SC4800–11 to determine the serial number (S/N) installed. And if— Then— In accordance with— None .................................. S/N 2324 or below is found installed. Replace the mode selector valve position transducer (MVT) of the elevator servo controls with a new MVT. Paragraphs 3.A.(2) and 3.B.(2) of the Accomplishment Instructions of Goodrich Actuation Systems Service Bulletin SC4800–27–16, Revision 3, dated May 19, 2006. Note 4: Airbus Service Bulletins A330–27– 3128 and A340–27–4129 refer to Goodrich Actuation Systems Service Bulletin SC4800– 27–16, Revision 3, dated May 19, 2006, as an additional source of service information for accomplishing the modification of the four elevator servo controls. (n) Prior to or concurrently with the replacement, if required, specified in paragraph (m)(2) of this AD, replace the eyeend equipped with a self-lubricated bearing with a new eye-end equipped with a roller bearing, grease the new eye-end, and reidentify the servo control, in accordance with paragraph 2.A. of the Accomplishment Instructions of TRW Service Bulletin SC4800–27–34–09, Revision 1, dated November 9, 2001. (o) Accomplishing all of the applicable actions required by paragraphs (m) and (n) of this AD constitutes terminating action for paragraphs (f) through (k) of this AD. Alternative Methods of Compliance (AMOCs) (p)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Related Information (q) European Aviation Safety Agency airworthiness directive 2007–0011, dated January 9, 2007, also addresses the subject of this AD. Material Incorporated by Reference (r) You must use the applicable service information contained in Table 3 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. TABLE 3.—MATERIAL INCORPORATED BY REFERENCE Service Bulletin Revision level Airbus Service Bulletin A330–27–3115, including Appendix 01 ..................................................... Airbus Service Bulletin A330–27–3128 ........................................................................................... Airbus Service Bulletin A340–27–4119, including Appendix 01 ..................................................... Airbus Service Bulletin A340–27–4129 ........................................................................................... Airbus Service Bulletin A340–27–4131 ........................................................................................... Goodrich Actuation Systems Service Bulletin SC4800–27–16 ....................................................... TRW Service Bulletin SC4800–27–34–09 ...................................................................................... 03 .............................. Original ...................... 03 .............................. Original ...................... Original ...................... 3 ................................ 1 ................................ Goodrich Actuation Systems Service Bulletin SC4800–27–16, Revision 3, contains the following effective pages: Page No. 1, 6, 8 ........ 2–5, 7 ......... Revision level shown on page Original ...... 3 ................. Date shown on page May 9, 2005. May 19, 2006. DEPARTMENT OF TRANSPORTATION Issued in Renton, Washington, on February 28, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–4488 Filed 3–11–08; 8:45 am] Federal Aviation Administration jlentini on PROD1PC65 with RULES Jkt 214001 PO 00000 14 CFR Part 39 [Docket No. FAA–2007–29342; Directorate Identifier 2007–SW–08–AD; Amendment 39– 15411; AD 2008–05–17] RIN 2120–AA64 BILLING CODE 4910–13–P 17:40 Mar 11, 2008 April 22, 2005. May 3, 2005. April 22, 2005. May 3, 2005. February 21, 2005. May 19, 2006. November 9, 2001. www.archives.gov/federal-register/cfr/ibrlocations.html. (1) The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. (3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; 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:// VerDate Aug<31>2005 Date Airworthiness Directives; MD Helicopters, Inc. Model 600N Helicopters Federal Aviation Administration, DOT. ACTION: Final rule. AGENCY: SUMMARY: This document supersedes an existing airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model 600N helicopters. That AD currently requires interim initial and repetitive inspections of tailboom parts, installing Frm 00026 Fmt 4700 Sfmt 4700 E:\FR\FM\12MRR1.SGM 12MRR1 jlentini on PROD1PC65 with RULES Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations six inspection holes in the aft fuselage skin panels, installing tailboom attachment bolt washers, modifying both access covers, and replacing broken attachment bolts. The current AD also provides for modifying the fuselage aft section as an optional terminating action. This amendment requires modifying the fuselage aft section within the next 24 months to strengthen the tailboom attachment fittings and upper longerons. The actions specified by this AD are intended to prevent failure of the tailboom attachment fittings, separation of the tailboom from the helicopter, and subsequent loss of control of the helicopter. DATES: Effective April 16, 2008. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of April 16, 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 Internet 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: Jon Mowery, Aviation Safety Engineer, FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960 Paramount Blvd., Lakewood, California 90712, telephone (562) 627–5322, fax (562) 627–5210. SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 by superseding AD 2006–08–12, Amendment 39–14569 (71 FR 24808, April 27, 2006), which superseded AD 2001–24–51, Amendment 39–12706 (67 FR 17934, April 12, 2002), for the specified MDHI model helicopters was published in the Federal Register on October 19, 2007 (72 FR 59227). The action proposed to require modifying the fuselage aft section within the next 24 months to strengthen the tailboom attachment fittings and upper longerons. On January 12, 2004, MDHI issued Technical Bulletin (TB) TB600N–007 specifying procedures, tooling, replacement parts, and supplies needed VerDate Aug<31>2005 17:40 Mar 11, 2008 Jkt 214001 13097 for modifying the fuselage aft section and tailboom. TB600N–007R1, dated April 13, 2006, superseded TB600N–007 to correct some tooling, replacement parts, and supplies. TB600N–007R2, dated October 5, 2006, superseded TB600N–007R1 to correct tooling part numbers and re-sequence some assembly steps. These TBs specify that any aircraft complying with any of these revisions meets the intent of the other TBs. In AD 2006–08–12, we incorporated by reference TB600N–007R1, dated April 13, 2006. Since issuing that AD, MDHI has issued TB600N–007R2, dated October 5, 2006 (TB), which updates previous issues by further specifying procedures for modifying the fuselage aft section to strengthen the tailboom attachment fittings and upper longerons. This latest revision continues to caution that a high level of sheet metal expertise and experience is required to perform this modification. 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 adopting the rule as proposed. The FAA estimates that this AD will affect 18 helicopters of U.S. registry, and the required actions will take about 322 work hours to modify each helicopter at an average labor rate of $80 per work hour. Required parts will cost about $14,960 per helicopter. The manufacturer states in its TB that those complying with the TB within 3 years of the issue date are eligible for special pricing and technical assistance. Based on these figures, we estimate the total cost impact of the AD on U.S. operators to be $732,960, assuming no special pricing from the manufacturer. 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. 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, Authority: 49 U.S.C. 106(g), 40113, 44701. PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 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 § 39.13 [Amended] 2. Section 39.13 is amended by removing Amendment 39–14569 (71 FR 24808, April 27, 2006) and by adding a new airworthiness directive (AD), Amendment 39–15411, to read as follows: I 2008–05–17 MD Helicopters, Inc.: Amendment 39–15411, Docket No. FAA–2007–29342, Directorate Identifier 2007–SW–08–AD. Supersedes AD 2006– 08–12, Amendment 39–14569, Docket No. FAA–2006–24518, Directorate Identifier 2006–SW–10–AD. Applicability: Model 600N helicopters, serial numbers with a prefix ‘‘RN’’ and 003 through 058, that have not been modified in E:\FR\FM\12MRR1.SGM 12MRR1 13098 Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations jlentini on PROD1PC65 with RULES the fuselage aft section to strengthen the tailboom attachments and longerons per MD Helicopters (MDHI) Technical Bulletin (TB) TB600N–007, dated January 12, 2004; TB600N–007R1, dated April 13, 2006, or TB600N–007R2, dated October 5, 2006, certificated in any category. Compliance: Required within the next 24 months, unless accomplished previously. To prevent failure of the tailboom attachment fittings, separation of the tailboom from the helicopter, and subsequent loss of control of the helicopter, do the following: (a) Modify the fuselage aft section to strengthen the tailboom attach fittings and upper longerons by following paragraph 2, Accomplishment Instructions, of MDHI TB600N–007R2, dated October 5, 2006, except you are not required to contact the manufacturer. This modification to the fuselage aft section is terminating action for the requirements of this AD. (b) 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: Jon Mowery, Aviation Safety Engineer, Airframe Branch, 3960 Paramount Blvd., Lakewood, California 90712, telephone (562) 627–5322, fax (562) 627–5210, for information about previously approved alternative methods of compliance. (c) Modifying the fuselage aft section shall be done by following the specified portions of MD Helicopters Technical Bulletin (TB) TB600N–007R2, dated October 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, or on the Internet at https://www.mdhelicopters.com. 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/ code_of_federal_regulations/ ibr_locations.html. (d) This amendment becomes effective on April 16, 2008. Issued in Fort Worth, Texas, on February 27, 2008. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E8–4489 Filed 3–11–08; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 17:40 Mar 11, 2008 Jkt 214001 DEPARTMENT OF TRANSPORTATION SUPPLEMENTARY INFORMATION: Federal Aviation Administration Discussion 14 CFR Part 39 [Docket No. FAA–2007–0414; Directorate Identifier 2007–NM–340–AD; Amendment 39–15413; AD 2008–06–01] RIN 2120–AA64 Airworthiness Directives; Bombardier Model CL–600–2C10 (Regional Jet Series 700, 701, & 702), Model CL–600– 2D15 (Regional Jet Series 705), and CL–600–2D24 (Regional Jet Series 900) 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: Bombardier Aerospace has completed a system safety review of the aircraft fuel system against fuel tank safety standards * * *. [A]ssessment showed that supplemental maintenance tasks [for the fuel tank wiring harness installation, and the hydraulic system No. 3 temperature transducer, among other items] are required to prevent potential ignition sources inside the fuel system, which could result in a fuel tank explosion. * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective April 16, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 16, 2008. ADDRESSES: You may examine the AD docket on the Internet at https:// 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: Rocco Viselli, 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) 228–7331; fax (516) 794–5531. PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on January 4, 2008 (73 FR 830). (A correction of the rule was published in the Federal Register on January 31, 2008 (73 FR 5767).) That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Bombardier Aerospace has completed a system safety review of the aircraft fuel system against fuel tank standards introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002–043. The identified non-compliances were then assessed using Transport Canada Policy Letter No. 525–001, to determine if mandatory corrective action is required. The assessment showed that supplemental maintenance tasks [for the fuel tank wiring harness installation, and the hydraulic system No. 3 temperature transducer, among other items] are required to prevent potential ignition sources inside the fuel system, which could result in a fuel tank explosion. Revision has been made to Canadair Regional Jet Models CL–600–2C10, CL–600–2D15 and CL–600–2D24 Maintenance Requirements Manual, CSP B–053, Part 2, Section 3 ‘‘Fuel System Limitations’’ to introduce the required maintenance tasks. 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. Changes Made to This AD For standardization purposes, we have revised this AD in the following ways: • We revised paragraph (f)(1) of this AD to add a reference to ‘‘Transport Canada Civil Aviation (TCCA) (or its delegated agent)’’ for approval of a particular document. We also revised paragraph (f)(2) of this AD to specify that no alternative inspections or inspection intervals may be used unless they are part of a later approved revision of Section 3, ‘‘Fuel System Limitations,’’ of Part 2 of Bombardier CL–600–2C10, CL–600–2D15, and CL–600–2D24 Maintenance Requirements Manual CSP E:\FR\FM\12MRR1.SGM 12MRR1

Agencies

[Federal Register Volume 73, Number 49 (Wednesday, March 12, 2008)]
[Rules and Regulations]
[Pages 13096-13098]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-4489]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-29342; Directorate Identifier 2007-SW-08-AD; 
Amendment 39-15411; AD 2008-05-17]
RIN 2120-AA64


Airworthiness Directives; MD Helicopters, Inc. Model 600N 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This document supersedes an existing airworthiness directive 
(AD) for MD Helicopters, Inc. (MDHI) Model 600N helicopters. That AD 
currently requires interim initial and repetitive inspections of 
tailboom parts, installing

[[Page 13097]]

six inspection holes in the aft fuselage skin panels, installing 
tailboom attachment bolt washers, modifying both access covers, and 
replacing broken attachment bolts. The current AD also provides for 
modifying the fuselage aft section as an optional terminating action. 
This amendment requires modifying the fuselage aft section within the 
next 24 months to strengthen the tailboom attachment fittings and upper 
longerons. The actions specified by this AD are intended to prevent 
failure of the tailboom attachment fittings, separation of the tailboom 
from the helicopter, and subsequent loss of control of the helicopter.

DATES: Effective April 16, 2008.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 16, 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 Internet 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: Jon Mowery, Aviation Safety Engineer, 
FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960 
Paramount Blvd., Lakewood, California 90712, telephone (562) 627-5322, 
fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 by 
superseding AD 2006-08-12, Amendment 39-14569 (71 FR 24808, April 27, 
2006), which superseded AD 2001-24-51, Amendment 39-12706 (67 FR 17934, 
April 12, 2002), for the specified MDHI model helicopters was published 
in the Federal Register on October 19, 2007 (72 FR 59227). The action 
proposed to require modifying the fuselage aft section within the next 
24 months to strengthen the tailboom attachment fittings and upper 
longerons.
    On January 12, 2004, MDHI issued Technical Bulletin (TB) TB600N-007 
specifying procedures, tooling, replacement parts, and supplies needed 
for modifying the fuselage aft section and tailboom. TB600N-007R1, 
dated April 13, 2006, superseded TB600N-007 to correct some tooling, 
replacement parts, and supplies. TB600N-007R2, dated October 5, 2006, 
superseded TB600N-007R1 to correct tooling part numbers and re-sequence 
some assembly steps. These TBs specify that any aircraft complying with 
any of these revisions meets the intent of the other TBs.
    In AD 2006-08-12, we incorporated by reference TB600N-007R1, dated 
April 13, 2006. Since issuing that AD, MDHI has issued TB600N-007R2, 
dated October 5, 2006 (TB), which updates previous issues by further 
specifying procedures for modifying the fuselage aft section to 
strengthen the tailboom attachment fittings and upper longerons. This 
latest revision continues to caution that a high level of sheet metal 
expertise and experience is required to perform this modification.
    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 adopting 
the rule as proposed.
    The FAA estimates that this AD will affect 18 helicopters of U.S. 
registry, and the required actions will take about 322 work hours to 
modify each helicopter at an average labor rate of $80 per work hour. 
Required parts will cost about $14,960 per helicopter. The manufacturer 
states in its TB that those complying with the TB within 3 years of the 
issue date are eligible for special pricing and technical assistance. 
Based on these figures, we estimate the total cost impact of the AD on 
U.S. operators to be $732,960, assuming no special pricing from the 
manufacturer.

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 removing Amendment 39-14569 (71 FR 
24808, April 27, 2006) and by adding a new airworthiness directive 
(AD), Amendment 39-15411, to read as follows:

2008-05-17 MD Helicopters, Inc.: Amendment 39-15411, Docket No. FAA-
2007-29342, Directorate Identifier 2007-SW-08-AD. Supersedes AD 
2006-08-12, Amendment 39-14569, Docket No. FAA-2006-24518, 
Directorate Identifier 2006-SW-10-AD.

    Applicability: Model 600N helicopters, serial numbers with a 
prefix ``RN'' and 003 through 058, that have not been modified in

[[Page 13098]]

the fuselage aft section to strengthen the tailboom attachments and 
longerons per MD Helicopters (MDHI) Technical Bulletin (TB) TB600N-
007, dated January 12, 2004; TB600N-007R1, dated April 13, 2006, or 
TB600N-007R2, dated October 5, 2006, certificated in any category.
    Compliance: Required within the next 24 months, unless 
accomplished previously.
    To prevent failure of the tailboom attachment fittings, 
separation of the tailboom from the helicopter, and subsequent loss 
of control of the helicopter, do the following:
    (a) Modify the fuselage aft section to strengthen the tailboom 
attach fittings and upper longerons by following paragraph 2, 
Accomplishment Instructions, of MDHI TB600N-007R2, dated October 5, 
2006, except you are not required to contact the manufacturer. This 
modification to the fuselage aft section is terminating action for 
the requirements of this AD.
    (b) 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: Jon Mowery, Aviation Safety Engineer, Airframe Branch, 3960 
Paramount Blvd., Lakewood, California 90712, telephone (562) 627-
5322, fax (562) 627-5210, for information about previously approved 
alternative methods of compliance.
    (c) Modifying the fuselage aft section shall be done by 
following the specified portions of MD Helicopters Technical 
Bulletin (TB) TB600N-007R2, dated October 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, or on the Internet at 
https://www.mdhelicopters.com. 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/code_of_federal_regulations/
ibr_locations.html.
    (d) This amendment becomes effective on April 16, 2008.

    Issued in Fort Worth, Texas, on February 27, 2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
 [FR Doc. E8-4489 Filed 3-11-08; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.