Airworthiness Directives; MD Helicopters, Inc. Model 600N Helicopters, 24808-24812 [06-3986]

Download as PDF 24808 Federal Register / Vol. 71, No. 81 / Thursday, April 27, 2006 / Rules and Regulations businesses, but the impact will not be significant. This rule is expected to benefit small and large horse entities in Indiana through trade opportunities already provided to States currently approved to receive horses from CEM-affected regions. Horses from CEM-affected regions will be allowed to be moved directly into Indiana, thereby benefitting Indiana importers through lower transport costs and reduced paperwork burdens. Mainly, breeding horse importers in Indiana would benefit from this rule. Because the pool of imported horses is a very small fraction of the domestic total and Indiana importers are expected to compete with importers in 21 other States, any net beneficial impact would be very small, especially when compared to the value of the imported horses. Under these circumstances, the Administrator of the Animal and Plant Health Inspection Service has determined that this action will not have a significant economic impact on a substantial number of small entities. Executive Order 12988 This rule has been reviewed under Executive Order 12988, Civil Justice Reform. This rule: (1) Preempts all State and local laws and regulations that are inconsistent with this rule; (2) has no retroactive effect; and (3) does not require administrative proceedings before parties may file suit in court challenging this rule. Paperwork Reduction Act This rule contains no new information collection or recordkeeping requirements under the Paperwork Reduction Act of 1995 (44 U.S.C. 3501 et seq.). List of Subjects in 9 CFR Part 93 Animal diseases, Imports, Livestock, Poultry and poultry products, Quarantine, Reporting and recordkeeping requirements. I Accordingly, 9 CFR part 93 is amended as follows: rmajette on PROD1PC67 with RULES PART 93—IMPORTATION OF CERTAIN ANIMALS, BIRDS, AND POULTRY, AND CERTAIN ANIMAL, BIRD, AND POULTRY PRODUCTS; REQUIREMENTS FOR MEANS OF CONVEYANCE AND SHIPPING CONTAINERS 1. The authority citation for part 93 continues to read as follows: I Authority: 7 U.S.C. 1622 and 8301–8317; 21 U.S.C. 136 and 136a; 31 U.S.C. 9701; 7 CFR 2.22, 2.80, and 371.4. VerDate Aug<31>2005 12:39 Apr 26, 2006 Jkt 208001 § 93.301 [Amended] 2. Section 93.301 is amended as follows: I a. In paragraph (h)(6), by adding, in alphabetical order, ‘‘The State of Indiana’’. I b. In paragraph (h)(7), by adding, in alphabetical order, ‘‘The State of Indiana’’. I Done in Washington, DC, this 21st day of April 2006. Kevin Shea, Acting Administrator, Animal and Plant Health Inspection Service. [FR Doc. 06–3985 Filed 4–26–06; 8:45 am] BILLING CODE 3410–34–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 [Docket No. NM316, Special Conditions No. 25–315–SC] Special Conditions: Airbus Model A380–800 Airplane; Discrete Gust Requirements confusion, a new Special Condition No., 25–315–SC, has been assigned to ‘‘Special Conditions: Airbus Model A380–800 Airplane, Discrete Gust Requirements.’’ Since no other part of the regulatory information has been changed, the Special Conditions are not being republished. Correction In Final Special Conditions document [FR Doc. 06–598, Filed 1–23–06; 8:45] and published on January 24, 2006 (71 FR 3753), make the following correction: 1. On page 3753, in the first column in the Headings section, correct ‘‘Special Conditions No. 25–312–SC’’ to read ‘‘Special Conditions No. 25–315– SC.’’ Issued in Renton, Washington, on April 6, 2006. Kevin Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–3947 Filed 4–26–06; 8:45 am] BILLING CODE 4910–13–M Federal Aviation Administration, DOT. ACTION: Final special conditions; correction. DEPARTMENT OF TRANSPORTATION This document corrects an error that appeared in Docket No. NM316, Special Conditions No. 25– 312–SC, which were published in the Federal Register on January 24, 2006 (71 FR 3753). The error is in the Special Conditions No. and is being corrected herein. [Docket No. FAA–2006–24518; Directorate Identifier 2006–SW–10–AD; Amendment 39– 14569; AD 2006–08–12] AGENCY: SUMMARY: Effective Date: The effective date of this correction is April 6, 2006. FOR FURTHER INFORMATION CONTACT: Madeleine Kolb, FAA, Standardization Branch, ANM–113, Transport Airplane Directorate, Aircraft Certifications Service, 1601 Lind Avenue, SW., Renton, WA 98055–4056; telephone (425) 227–2799; facsimile (425) 227– 1149. DATES: The document designated as ‘‘Docket No. NM316, Special Conditions No. 25– 312–SC’’ was published in the Federal Register on January 24, 2006 (71 FR 3753). The document issued special conditions pertaining to discrete gust requirements for the Airbus Model A380–800 airplane. As published, the document contained an error in that the Special Conditions No. was shown as 25–312– SC, which is the number of a different set of special conditions. To avoid SUPPLEMENTARY INFORMATION: PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Federal Aviation Administration 14 CFR Part 39 RIN 2120–AA64 Airworthiness Directives; MD Helicopters, Inc. Model 600N Helicopters Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. AGENCY: SUMMARY: This amendment supersedes an existing airworthiness directive (AD) for the MD Helicopters, Inc. (MDHI) Model 600N helicopters, that currently requires inspecting both upper tailboom attachment fittings, nut plates and both angles for a crack or thread damage, and repairing or replacing any cracked or damaged part. That AD also requires replacing the upper right tailboom attachment bolt with a new attachment bolt, and if the upper right attachment bolt is broken, replacing the three remaining attachment bolts with airworthy bolts. Adding a washer to each bolt and modifying both access covers is also required. Thereafter, inspecting the upper tailboom attachments and repairing or replacing E:\FR\FM\27APR1.SGM 27APR1 Federal Register / Vol. 71, No. 81 / Thursday, April 27, 2006 / Rules and Regulations any cracked part is required by that AD. That AD was prompted by the discovery of a cracked attachment bolt on a helicopter. This AD requires those same actions, plus installing additional inspection holes in the aft fuselage skin panels and inspecting the upper and lower tailboom attachment fittings, the upper longerons, and the angles and nut plates for cracks. It also requires, within a specified time, replacing the upper right tailboom attachment fitting, painting the inspection area, and replacing existing nut plates. Additionally, it requires inspecting the attachment bolts for any damage or wear. This amendment is prompted by an accident involving a Model 600N helicopter. 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. Effective April 27, 2006. The incorporation by reference of MD Helicopters Service Bulletin SB600N– 039, dated December 9, 2003; MD Helicopters Service Bulletin SB600N– 043, dated April 13, 2006; and MD Helicopters Technical Bulletin TB600N–007, Revision 1, dated April 13, 2006, as listed in the regulations, is approved by the Director of the Federal Register as of April 27, 2006. The incorporation by reference of MD Helicopters Service Bulletin SB600N– 036, dated November 2, 2001, as listed in the regulations, was approved previously by the Director of the Federal Register as of April 29, 2002 (67 FR 17934, April 12, 2002). Comments for inclusion in the Rules Docket must be received on or before June 26, 2006. ADDRESSES: Use one of the following addresses to submit comments on this AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically; • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically; • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590; • Fax: (202) 493–2251; or • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this AD from MD rmajette on PROD1PC67 with RULES DATES: VerDate Aug<31>2005 12:39 Apr 26, 2006 Jkt 208001 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 the AD, any comments, and other information on the Internet at https://dms.dot.gov, or in person at the Docket Management System (DMS) Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. 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: On April 12, 2002, the FAA published AD 2001– 24–51, Amendment 39–12706 (67 FR 17934), applicable to MDHI Model 600N helicopters, that had been issued on November 28, 2001, to all known operators. That AD requires, within 5 hours time-in-service (TIS), inspecting both upper tailboom attachment fittings, nut plates, and both angles for a crack or thread damage, and repairing or replacing any cracked or damaged part before further flight. That AD also requires replacing the upper right tailboom attachment bolt with a new bolt, and if the upper right tailboom attachment bolt is broken, replacing the three remaining attachment bolts with airworthy attachment bolts before further flight. Adding a washer to each bolt and modifying both access covers was also required. Thereafter, inspecting the upper tailboom attachments at intervals not to exceed 25 hours TIS and repairing or replacing any cracked part is required by that AD. That AD was prompted by the discovery of a cracked attachment bolt on a helicopter. That condition, if not corrected, could result in failure of a tailboom attachment, loss of the tailboom, and subsequent loss of control of the helicopter. Since issuing that AD, on March 21, 2006, an accident occurred in Alberta, Canada, involving an MDHI Model 600N helicopter, resulting in one fatality. That accident may have been caused by failure of the thread PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 24809 engagement between the nut plate and bolt, and/or by cracking in the attachment bathtub fitting. This condition, if not corrected, could result in failure of the tailboom attachment fittings, separation of the tailboom from the helicopter, and subsequent loss of control of the helicopter. On February 2, 2005, we issued a notice of proposed rulemaking (NPRM), applicable to MDHI Model 600N helicopters, to supersede AD 2001–24– 51. That NPRM, Docket No. 2004–SW– 16–AD (70 FR 7065, February 10, 2005), proposed to require the same actions required by AD 2001–24–51, and also proposed to require, before further flight, installing six additional inspection holes in the aft fuselage skin panels. The NPRM also proposed to require, within 100 hours TIS, inspecting the lower tailboom attachment fittings, inspecting the upper longerons at intervals not to exceed 1,200 flight hours, and additionally proposed a terminating action of modifying the fuselage aft section to strengthen the tailboom attachments and longerons. We anticipate withdrawing that NPRM. We also anticipate issuing a subsequent AD to require, within 24 months TIS, modifying the aft fuselage to strengthen the tailboom attachments and the longerons. We have reviewed the following MDHI service information: • MD Helicopters Service Bulletin SB600N–036, dated November 2, 2001, which describes procedures for inspecting the tailboom attachment fittings, repairing damaged fittings, and installing inspection holes in the upper right and upper left access covers; • MD Helicopters Service Bulletin SB600N–039, dated December 9, 2003, which describes procedures for installing additional inspection holes in the fuselage, and also describes procedures for recurring inspections of the tailboom attachment fittings and of the upper longerons for cracks; and • MD Helicopters Service Bulletin SB600N–043, dated April 13, 2006, which describes procedures for inspecting the tailboom attachment fittings and attachment bolts, and replacing the nut plates, attachment fittings, and attachment bolts, if necessary. • MD Helicopters Technical Bulletin TB600N–007, Revision 1, dated April 13, 2006, which describes procedures for modifying the fuselage aft section to strengthen tailboom attachment fittings and upper longerons. Since an unsafe condition has been identified that is likely to exist or develop on other MDHI Model 600N E:\FR\FM\27APR1.SGM 27APR1 rmajette on PROD1PC67 with RULES 24810 Federal Register / Vol. 71, No. 81 / Thursday, April 27, 2006 / Rules and Regulations helicopters of the same type design, this AD supersedes AD 2001–24–51 to require, within 5 hours TIS, installing six inspection holes in the aft fuselage skin panels. Then, using a borescope, inspect all four tailboom attachment fittings and the surrounding areas, the upper longerons, the upper nut plates and the upper angles for cracks. Add a washer to each bolt between the tailboom and the NAS1587 countersunk washer. If a crack is found on a righthand angle, before further flight, install a new clip. If a crack is found on the left-hand angle, before further flight, replace the angle with an airworthy angle, or repair the angle in accordance with FAA-approved procedures. Finally, replacing the upper RH tailboom attachment bolt with a new bolt, and if the upper right attachment bolt is broken, replacing the three remaining attachment bolts with airworthy attachment bolts before further flight is required. Within 25 hours TIS, the following actions are also required: • Inspecting all attachment fittings and surrounding areas; • Replacing the upper right tailboom attachment fitting with an airworthy fitting; • Painting the inspection area; • Inspecting the attachment bolts for wear or damage; • Replacing worn or damaged attachment bolts; and • Replacing all existing nut plates with airworthy nut plates. Thereafter, inspect the upper tailboom attachment fittings, angles, and nut plates at intervals not to exceed 25 hours TIS, and inspect the lower tailboom attachment fittings, angles and nut plates at intervals not to exceed 100 hours TIS. Modifying the aft fuselage to strengthen the tailboom attachments and the longerons constitutes a terminating action for the requirements of this AD. Accomplish the actions by following the specified portions of the service and technical bulletins described previously. The short compliance time involved is required because the previously described critical unsafe condition can adversely affect the controllability and structural integrity of the helicopter. A portion of the helicopters operated in this fleet have high utilization rates. Drilling inspection holes and inspecting the tailboom attachment fittings and surrounding areas for cracks are required within 5 hours TIS, therefore this AD must be issued immediately. Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment VerDate Aug<31>2005 12:39 Apr 26, 2006 Jkt 208001 hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days. The FAA estimates that this AD will affect 18 helicopters, and: • Initial inspections will take approximately 2 work hours; • Repetitive inspections will take approximately 24 work hours; and • The initial modification will take approximately 25 work hours for a total of 51 work hours per helicopter to accomplish at an average labor rate of $80 per work hour. Required parts will cost approximately $2,050 for each tailboom attachment fitting (1 per helicopter) and $26 for 4 nut plates and 4 rivet collars per helicopter. Based on these figures, which assume a rate of utilization of 600 hours TIS per year, resulting in 24 repetitive inspections per year, we estimate the total cost impact of the AD on U.S. operators to be approximately $6,156 per helicopter, or $110,808, for the fleet, to perform the inspections and replacements. Comments Invited This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2006–24518; Directorate Identifier 2006–SW–10–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Using the search function of our docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent the comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https://dms.dot.gov. 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 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 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 DMS 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 removing Amendment 39–12706 (71 FR 17934, April 12, 2002), and by adding I E:\FR\FM\27APR1.SGM 27APR1 Federal Register / Vol. 71, No. 81 / Thursday, April 27, 2006 / Rules and Regulations a new airworthiness directive (AD), Amendment 39–14569, to read as follows: 2006–08–12 MD Helicopters, Inc: Amendment 39–14569. Docket No. FAA–2006–24518; Directorate Identifier 2006–SW–10–AD. Supersedes AD 2001– 24–51, Amendment 39–12706, Docket No. 2001–SW–57–AD. rmajette on PROD1PC67 with RULES Applicability Model 600N helicopters, serial numbers with a prefix ‘‘RN’’ and 003 through 058, that have not been modified in the fuselage aft section to strengthen the tailboom attachments and longerons in accordance with MD Helicopters Technical Bulletin TB600N–007, dated January 12, 2004, or TB600N–007, Revision 1, dated April 13, 2006, certificated in any category. Compliance Required as indicated. To prevent failure of the tailboom attachment fittings, separation of the tailboom from the helicopter, and subsequent loss of control of the helicopter, accomplish the following: Note 1: There is a slight discrepancy between MD Helicopters, Inc. Service Bulletin SB600N–036, dated November 2, 2001 (SB600N–036) and MD Helicopters Service Bulletin SB600N–039, dated December 9, 2003 (SB600N–039) on the vertical location of the upper left inspection hole. Either location is acceptable for this AD. (a) Within 5 hours time-in-service (TIS), unless accomplished previously: (1) Remove the tailboom fairing and tailboom. Remove both upper tailboom attachment access covers in accordance with the Accomplishment Instructions, paragraph 2.B.(2) of SB600N–036. Note 2: MDHI CSP–HMI–2, Section 53–40– 30, pertains to the subject of this AD. (2) Using a light and a 10x or higher magnifying glass: (i) Inspect the right and left upper tailboom attachment fittings, part number (P/N) 500N3422 and 500N3422–3, respectively, for a crack as shown in Figure 1 of the SB600N– 036. If a crack is found, replace any cracked attachment fitting with an airworthy attachment fitting before further flight. (ii) Inspect both upper tailboom attachment nut plates for thread damage or a crack. Replace any damaged or cracked nut plate with an airworthy nut plate before further flight. (iii) Inspect both angles for a crack. If a crack is found on a right-hand angle, P/N 500N3429–6, before further flight, install a new clip in accordance with the Accomplishment Instructions, paragraph 2.B.(5)(c) of the SB600N–036. If a crack is found on the left-hand angle, P/N 500N3429– 7, before further flight, replace the angle with an airworthy angle, or repair the angle in accordance with FAA-approved procedures. (3) Replace the upper right (pilot side) tailboom attachment bolt (bolt) with a new bolt. (4) If the removed upper right pilot-side bolt is broken, replace the remaining three VerDate Aug<31>2005 12:39 Apr 26, 2006 Jkt 208001 bolts with airworthy bolts before further flight. (5) Add one washer, P/N AN960C516 (NAS1149C0563R) or AN960C616 (NAS1149C0663R), as appropriate, to each tailboom bolt between the tailboom and the NAS1587 countersunk washer. A minimum of two threads must extend past the nut plate. (6) Modify both access covers in accordance with the Accomplishment Instructions, paragraph 2.B.(6), of the SB600N–036. (b) Within 5 hours TIS, unless accomplished previously: (1) Drill four additional inspection holes in the fuselage as shown for the left side of the fuselage in Figure 1 of SB600N–039, by following the Accomplishment Instruction paragraphs of SB600N–039 as follows: (i) Paragraphs 2.A.(1)(a), (b), and (d) for inspection holes at L166 and R166. (ii) Paragraphs 2.A.(2)(a), (b), and (d) for inspection holes at L153 and R153. (2) Thoroughly clean the attachment fittings and surrounding area. If the attachment fittings and surrounding area cannot be satisfactorily cleaned to accomplish a borescope inspection, then accomplish the actions in paragraph (c) of this AD. (3) Using a lighted borescope, inspect all four attachment fittings and the surrounding area for cracking. (i) If a crack is found in the upper right attachment fitting, accomplish the actions in paragraph (c) of this AD. (ii) If a crack is found in any of the other three attachment fittings, before further flight, accomplish the actions described in paragraph (f) of this AD. (4) Visually inspect the upper longerons for cracking in accordance with the Accomplishment Instructions, paragraph 2.C., of SB600N–039. If a crack is found in the upper longeron, accomplish the actions in paragraph (e) of this AD. Note 3: The reference in Figure 1 of SB600N–039 to the inspection hole at L167 mistakenly states that it was ‘‘Added by SB900–036.’’ Inspection holes at L167 and R167 were originally specified by SB600N– 036. (c) Within 25 hours TIS, unless accomplished previously: (1) Thoroughly clean all attachment fittings and the surrounding areas, inspect the area for cracking, replace the upper right attachment fitting and all four nut plates, and paint the area inside of the attachment fittings in accordance with the Accomplishment Instructions, paragraph 2.B., of MD Helicopters Service Bulletin SB600N–043, dated April 13, 2006 (SB600N– 043). If a crack is found in any of the other three attachment fittings, before further flight, accomplish the actions described in paragraph (f) of this AD. (2) Using a 10x magnifying glass, inspect the attachment bolts’ threads and shanks for wear or damage in accordance with paragraph 2.B., of SB600N–043. If wear or damage is present, replace the attachment bolts with airworthy bolts. (d) Thereafter, at the specified intervals, remove the plug buttons from the inspection PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 24811 holes, and using a bright light, inspect the upper and lower left and upper and lower right attachment fittings, angles, and nut plates for a crack by following the Accomplishment Instruction paragraphs of SB600N–039, as follows, except you are not required to contact MDHI to meet the requirements of this AD. (1) At intervals not to exceed 25 hours TIS, through inspection holes at L167 and R167, inspect the upper left and upper right attachment fittings, angles, and nut plates by following the Accomplishment Instructions, paragraphs 2.B.(2) through 2.B.(4), of SB600N–039. (2) At intervals not to exceed 100 hours TIS, through inspection holes at L166 and R166, inspect the lower left and lower right attachment fittings, angles, and nut plates by following the Accomplishment Instructions, paragraphs 2.B.(2) through 2.B.(4), of SB600N–039. (e) If a crack is found in the upper right attachment fitting, or in any angle, nut plate, longeron, or if thread wear or damage is found on any nut plate or bolt, before further flight, replace the cracked or worn or damaged part with an appropriate airworthy part, or accomplish the actions in paragraph (f) of this AD. If cracking is found in any of the other three attachment fittings, before further flight, accomplish the actions described in paragraph (f) of this AD. (f) If required by paragraph (c)(1) of this AD, or if you choose to make this modification to comply with paragraph (e) of this AD, modify the aft fuselage to strengthen the tailboom attachments and the longerons by following the Accomplishment Instructions of MD Helicopters Technical Bulletin TB600N–007, Revision 1, dated April 13, 2006. Modifying the aft fuselage in accordance with this paragraph constitutes a terminating action for the requirements of this AD. (g) 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, Airframe Branch, FAA, ATTN: Jon Mowery, Aviation Safety Engineer, 3960 Paramount Blvd., Lakewood, California 90712, telephone (562) 627–5322, fax (562) 627–5210, for information about previously approved alternative methods of compliance. (h) Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the helicopter to the nearest maintenance facility capable of performing the inspections and modification. (i) The inspections shall be done in accordance with MD Helicopters Service Bulletin SB600N–036, dated November 2, 2001. The incorporation by reference of that document was approved previously by the Director of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, as of April 29, 2002 (67 FR 17934, April 12, 2002). The inspections, replacements and modifications shall be done in accordance with MD Helicopters Service Bulletin SB600N–039, dated December 9, 2003; MD Helicopters Service Bulletin SB600N–043, dated April 13, 2006; and MD Helicopters Technical Bulletin E:\FR\FM\27APR1.SGM 27APR1 24812 Federal Register / Vol. 71, No. 81 / Thursday, April 27, 2006 / Rules and Regulations TB600N–007, Revision 1, dated April 13, 2006. The incorporation by reference of these documents was approved by the Director of the Federal Register 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 web at www.mdhelicopters.com. Copies may be inspected 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. (j) This amendment becomes effective on April 27, 2006. 2006, to coincide with the IFR Enroute Low Altitude charting date. The FAA uses the direct final rulemaking procedure for a non-controversial rule where the FAA believes that there will be no adverse public comment. This direct final rule advised the public that no adverse comments were anticipated, and that unless a written adverse comment, or written notice of intent to submit such an adverse comment, were received within the comment period, the regulation will become effective on June 8, 2006, as per the final rule correction. No adverse comments were received, and thus this notice confirms that this direct final rule will become effective on that date. Issued in Fort Worth, Texas, on April 20, 2006. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 06–3986 Filed 4–26–06; 8:45 am] Issued in Los Angeles, California, on April 12, 2006. Tony DiBernardo, Manager, Resource Management Branch, AWP–540, Western Terminal Operations. [FR Doc. 06–3948 Filed 4–26–06; 8:45 am] BILLING CODE 4910–13–P BILLING CODE 4910–13–M DEPARTMENT OF TRANSPORTATION SOCIAL SECURITY ADMINISTRATION Federal Aviation Administration 20 CFR Part 404 14 CFR Part 71 RIN 0960–AG32 [Docket No. FAA–2005–23271; Airspace Docket No. 05–AWP–15] Filing of Applications and Requirements for Widow’s and Widower’s Benefits RIN 2120–AA66 Establishment of Class E Enroute Domestic Airspace Area, Vandenberg AFB, CA Federal Aviation Administration (FAA), DOT. ACTION: Direct final rule, confirmation of effective date. rmajette on PROD1PC67 with RULES AGENCY: SUMMARY: This document confirms the effective date of the direct final rule which establishes a Class E enroute domestic airspace area, Vandenberg AFB, CA, to replace existing Class G uncontrolled airspace. DATES: Effective Date: 0901 UTC June 8, 2006. FOR FURTHER INFORMATION CONTACT: Francie Hope, Western Terminal Operations Airspace Specialist, AWP– 520.3, Federal Aviation Administration, 15000 Aviation Boulevard, Lawndale, California 90261, telephone (310) 725– 6502. SUPPLEMENTARY INFORMATION: The FAA published this direct final rule with a request for comments in the Federal Register on March 7, 2006 (71 FR 11297). In addition, a correction to the direct final rule was published in the Federal Register on March 24, 2006, changing the effective date to June 8, VerDate Aug<31>2005 12:39 Apr 26, 2006 Jkt 208001 Social Security Administration. Final rule. AGENCY: ACTION: SUMMARY: We are revising one of our regulations to clarify that we will protect a title II claimant’s filing date as of the date the claimant or other proper applicant on the claimant’s behalf completes and transmits to the Social Security Administration (SSA) the Personal Information Identification data on the Internet Social Security Benefit Application (ISBA). This revision addresses an aspect of implementing the ISBA to provide certain rights to Internet filers that we afford to other filers. In addition, we are correcting one word in a different title II regulation. The revision is necessary to correctly reflect the circumstances under which a claimant for widow’s or widower’s benefits as the insured person’s surviving divorced spouse would be considered ‘‘unmarried.’’ DATES: This final rule is effective on April 27, 2006. FOR FURTHER INFORMATION CONTACT: Lola Doyle, Social Insurance Specialist, Office of Income Security Programs, Mary Jayne Neubauer, Social Insurance Specialist, Office of Income Security PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Programs or Peter F. White, Social Insurance Specialist, Office of Income Security Programs, Social Security Administration, 252 Altmeyer Building, 6401 Security Boulevard, Baltimore, MD 21235–6401, 410–965–5899 or TTY 1– 800–966–5609, for information about this Federal Register document. For information on eligibility or filing for benefits, call our national toll-free number, 1–800–772–1213 or TTY 1– 800–325–0778, or visit our Internet site, Social Security Online, at https:// www.socialsecurity.gov. SUPPLEMENTARY INFORMATION: Electronic Version The electronic file of this document is available on the date of publication in the Federal Register on the Internet site for the Government Printing Office at https://www.gpoaccess.gov/fr/ index.html. Background Various sections of the Social Security Act (Act) and § 404.603 of our regulations provide that filing an application with SSA is one of the requirements for entitlement to Federal old-age, survivors and disability insurance benefits. A valid application may only be signed by a proper applicant as defined in our regulations. Section 404.612 of our regulations specifies who may sign an application. If the claimant becomes entitled to any past-due benefits, we pay the past-due benefits in accordance with the Act based upon the filing date of the application. We have long recognized, however, that an individual might intend to file a claim for benefits but be unable to complete an application immediately. Accordingly, § 404.630 of our regulations provides that any proper applicant may establish an earlier ‘‘protective’’ filing date based upon that individual’s initial contact with us. If all of the requirements for a protective filing are satisfied, we will establish the date of the initial contact as the protective filing date of the application. Among the requirements for preserving the protective filing date, § 404.630(c) provides that a proper applicant must file a signed application with us within six months of the date we notify the claimant or other person listed in § 404.612 about the need to file an application. This protective filing date prevents a potential loss of any retroactive benefits. Our regulations currently do not explain how we determine a claimant’s application filing date when a proper applicant intends to file a benefit claim E:\FR\FM\27APR1.SGM 27APR1

Agencies

[Federal Register Volume 71, Number 81 (Thursday, April 27, 2006)]
[Rules and Regulations]
[Pages 24808-24812]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-3986]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24518; Directorate Identifier 2006-SW-10-AD; 
Amendment 39-14569; AD 2006-08-12]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) for the MD Helicopters, Inc. (MDHI) Model 600N helicopters, that 
currently requires inspecting both upper tailboom attachment fittings, 
nut plates and both angles for a crack or thread damage, and repairing 
or replacing any cracked or damaged part. That AD also requires 
replacing the upper right tailboom attachment bolt with a new 
attachment bolt, and if the upper right attachment bolt is broken, 
replacing the three remaining attachment bolts with airworthy bolts. 
Adding a washer to each bolt and modifying both access covers is also 
required. Thereafter, inspecting the upper tailboom attachments and 
repairing or replacing

[[Page 24809]]

any cracked part is required by that AD. That AD was prompted by the 
discovery of a cracked attachment bolt on a helicopter. This AD 
requires those same actions, plus installing additional inspection 
holes in the aft fuselage skin panels and inspecting the upper and 
lower tailboom attachment fittings, the upper longerons, and the angles 
and nut plates for cracks. It also requires, within a specified time, 
replacing the upper right tailboom attachment fitting, painting the 
inspection area, and replacing existing nut plates. Additionally, it 
requires inspecting the attachment bolts for any damage or wear. This 
amendment is prompted by an accident involving a Model 600N helicopter. 
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 27, 2006.
    The incorporation by reference of MD Helicopters Service Bulletin 
SB600N-039, dated December 9, 2003; MD Helicopters Service Bulletin 
SB600N-043, dated April 13, 2006; and MD Helicopters Technical Bulletin 
TB600N-007, Revision 1, dated April 13, 2006, as listed in the 
regulations, is approved by the Director of the Federal Register as of 
April 27, 2006.
    The incorporation by reference of MD Helicopters Service Bulletin 
SB600N-036, dated November 2, 2001, as listed in the regulations, was 
approved previously by the Director of the Federal Register as of April 
29, 2002 (67 FR 17934, April 12, 2002).
    Comments for inclusion in the Rules Docket must be received on or 
before June 26, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically;
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically;
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590;
     Fax: (202) 493-2251; or
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    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 the AD, any comments, and 
other information on the Internet at https://dms.dot.gov, or in person 
at the Docket Management System (DMS) Docket Offices between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The Docket 
Office (telephone (800) 647-5227) is located on the plaza level of the 
Department of Transportation Nassif Building at the street address 
stated in the ADDRESSES section. Comments will be available in the AD 
docket shortly after the DMS receives them.

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: On April 12, 2002, the FAA published AD 
2001-24-51, Amendment 39-12706 (67 FR 17934), applicable to MDHI Model 
600N helicopters, that had been issued on November 28, 2001, to all 
known operators. That AD requires, within 5 hours time-in-service 
(TIS), inspecting both upper tailboom attachment fittings, nut plates, 
and both angles for a crack or thread damage, and repairing or 
replacing any cracked or damaged part before further flight. That AD 
also requires replacing the upper right tailboom attachment bolt with a 
new bolt, and if the upper right tailboom attachment bolt is broken, 
replacing the three remaining attachment bolts with airworthy 
attachment bolts before further flight. Adding a washer to each bolt 
and modifying both access covers was also required. Thereafter, 
inspecting the upper tailboom attachments at intervals not to exceed 25 
hours TIS and repairing or replacing any cracked part is required by 
that AD. That AD was prompted by the discovery of a cracked attachment 
bolt on a helicopter. That condition, if not corrected, could result in 
failure of a tailboom attachment, loss of the tailboom, and subsequent 
loss of control of the helicopter.
    Since issuing that AD, on March 21, 2006, an accident occurred in 
Alberta, Canada, involving an MDHI Model 600N helicopter, resulting in 
one fatality. That accident may have been caused by failure of the 
thread engagement between the nut plate and bolt, and/or by cracking in 
the attachment bathtub fitting. This condition, if not corrected, could 
result in failure of the tailboom attachment fittings, separation of 
the tailboom from the helicopter, and subsequent loss of control of the 
helicopter.
    On February 2, 2005, we issued a notice of proposed rulemaking 
(NPRM), applicable to MDHI Model 600N helicopters, to supersede AD 
2001-24-51. That NPRM, Docket No. 2004-SW-16-AD (70 FR 7065, February 
10, 2005), proposed to require the same actions required by AD 2001-24-
51, and also proposed to require, before further flight, installing six 
additional inspection holes in the aft fuselage skin panels. The NPRM 
also proposed to require, within 100 hours TIS, inspecting the lower 
tailboom attachment fittings, inspecting the upper longerons at 
intervals not to exceed 1,200 flight hours, and additionally proposed a 
terminating action of modifying the fuselage aft section to strengthen 
the tailboom attachments and longerons. We anticipate withdrawing that 
NPRM. We also anticipate issuing a subsequent AD to require, within 24 
months TIS, modifying the aft fuselage to strengthen the tailboom 
attachments and the longerons.
    We have reviewed the following MDHI service information:
     MD Helicopters Service Bulletin SB600N-036, dated November 
2, 2001, which describes procedures for inspecting the tailboom 
attachment fittings, repairing damaged fittings, and installing 
inspection holes in the upper right and upper left access covers;
     MD Helicopters Service Bulletin SB600N-039, dated December 
9, 2003, which describes procedures for installing additional 
inspection holes in the fuselage, and also describes procedures for 
recurring inspections of the tailboom attachment fittings and of the 
upper longerons for cracks; and
     MD Helicopters Service Bulletin SB600N-043, dated April 
13, 2006, which describes procedures for inspecting the tailboom 
attachment fittings and attachment bolts, and replacing the nut plates, 
attachment fittings, and attachment bolts, if necessary.
     MD Helicopters Technical Bulletin TB600N-007, Revision 1, 
dated April 13, 2006, which describes procedures for modifying the 
fuselage aft section to strengthen tailboom attachment fittings and 
upper longerons.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other MDHI Model 600N

[[Page 24810]]

helicopters of the same type design, this AD supersedes AD 2001-24-51 
to require, within 5 hours TIS, installing six inspection holes in the 
aft fuselage skin panels. Then, using a borescope, inspect all four 
tailboom attachment fittings and the surrounding areas, the upper 
longerons, the upper nut plates and the upper angles for cracks. Add a 
washer to each bolt between the tailboom and the NAS1587 countersunk 
washer. If a crack is found on a right-hand angle, before further 
flight, install a new clip. If a crack is found on the left-hand angle, 
before further flight, replace the angle with an airworthy angle, or 
repair the angle in accordance with FAA-approved procedures. Finally, 
replacing the upper RH tailboom attachment bolt with a new bolt, and if 
the upper right attachment bolt is broken, replacing the three 
remaining attachment bolts with airworthy attachment bolts before 
further flight is required. Within 25 hours TIS, the following actions 
are also required:
     Inspecting all attachment fittings and surrounding areas;
     Replacing the upper right tailboom attachment fitting with 
an airworthy fitting;
     Painting the inspection area;
     Inspecting the attachment bolts for wear or damage;
     Replacing worn or damaged attachment bolts; and
     Replacing all existing nut plates with airworthy nut 
plates. Thereafter, inspect the upper tailboom attachment fittings, 
angles, and nut plates at intervals not to exceed 25 hours TIS, and 
inspect the lower tailboom attachment fittings, angles and nut plates 
at intervals not to exceed 100 hours TIS. Modifying the aft fuselage to 
strengthen the tailboom attachments and the longerons constitutes a 
terminating action for the requirements of this AD. Accomplish the 
actions by following the specified portions of the service and 
technical bulletins described previously.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability and structural integrity of the helicopter. A portion 
of the helicopters operated in this fleet have high utilization rates. 
Drilling inspection holes and inspecting the tailboom attachment 
fittings and surrounding areas for cracks are required within 5 hours 
TIS, therefore this AD must be issued immediately.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.
    The FAA estimates that this AD will affect 18 helicopters, and:
     Initial inspections will take approximately 2 work hours;
     Repetitive inspections will take approximately 24 work 
hours; and
     The initial modification will take approximately 25 work 
hours for a total of 51 work hours per helicopter to accomplish at an 
average labor rate of $80 per work hour. Required parts will cost 
approximately $2,050 for each tailboom attachment fitting (1 per 
helicopter) and $26 for 4 nut plates and 4 rivet collars per 
helicopter. Based on these figures, which assume a rate of utilization 
of 600 hours TIS per year, resulting in 24 repetitive inspections per 
year, we estimate the total cost impact of the AD on U.S. operators to 
be approximately $6,156 per helicopter, or $110,808, for the fleet, to 
perform the inspections and replacements.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any written data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2006-24518; 
Directorate Identifier 2006-SW-10-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the AD in light 
of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of our docket 
Web site, you can find and read the comments to any of our dockets, 
including the name of the individual who sent the comment. You may 
review the DOT's complete Privacy Act Statement in the Federal Register 
published on April 11, 2000 (65 FR 19477-78), or you may visit https://
dms.dot.gov.

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 DMS 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 39-12706 (71 FR 
17934, April 12, 2002), and by adding

[[Page 24811]]

a new airworthiness directive (AD), Amendment 39-14569, to read as 
follows:

2006-08-12 MD Helicopters, Inc: Amendment 39-14569. Docket No. FAA-
2006-24518; Directorate Identifier 2006-SW-10-AD. Supersedes AD 
2001-24-51, Amendment 39-12706, Docket No. 2001-SW-57-AD.

Applicability

    Model 600N helicopters, serial numbers with a prefix ``RN'' and 
003 through 058, that have not been modified in the fuselage aft 
section to strengthen the tailboom attachments and longerons in 
accordance with MD Helicopters Technical Bulletin TB600N-007, dated 
January 12, 2004, or TB600N-007, Revision 1, dated April 13, 2006, 
certificated in any category.

Compliance

    Required as indicated.
    To prevent failure of the tailboom attachment fittings, 
separation of the tailboom from the helicopter, and subsequent loss 
of control of the helicopter, accomplish the following:

    Note 1: There is a slight discrepancy between MD Helicopters, 
Inc. Service Bulletin SB600N-036, dated November 2, 2001 (SB600N-
036) and MD Helicopters Service Bulletin SB600N-039, dated December 
9, 2003 (SB600N-039) on the vertical location of the upper left 
inspection hole. Either location is acceptable for this AD.

    (a) Within 5 hours time-in-service (TIS), unless accomplished 
previously:
    (1) Remove the tailboom fairing and tailboom. Remove both upper 
tailboom attachment access covers in accordance with the 
Accomplishment Instructions, paragraph 2.B.(2) of SB600N-036.

    Note 2: MDHI CSP-HMI-2, Section 53-40-30, pertains to the 
subject of this AD.

    (2) Using a light and a 10x or higher magnifying glass:
    (i) Inspect the right and left upper tailboom attachment 
fittings, part number (P/N) 500N3422 and 500N3422-3, respectively, 
for a crack as shown in Figure 1 of the SB600N-036. If a crack is 
found, replace any cracked attachment fitting with an airworthy 
attachment fitting before further flight.
    (ii) Inspect both upper tailboom attachment nut plates for 
thread damage or a crack. Replace any damaged or cracked nut plate 
with an airworthy nut plate before further flight.
    (iii) Inspect both angles for a crack. If a crack is found on a 
right-hand angle, P/N 500N3429-6, before further flight, install a 
new clip in accordance with the Accomplishment Instructions, 
paragraph 2.B.(5)(c) of the SB600N-036. If a crack is found on the 
left-hand angle, P/N 500N3429-7, before further flight, replace the 
angle with an airworthy angle, or repair the angle in accordance 
with FAA-approved procedures.
    (3) Replace the upper right (pilot side) tailboom attachment 
bolt (bolt) with a new bolt.
    (4) If the removed upper right pilot-side bolt is broken, 
replace the remaining three bolts with airworthy bolts before 
further flight.
    (5) Add one washer, P/N AN960C516 (NAS1149C0563R) or AN960C616 
(NAS1149C0663R), as appropriate, to each tailboom bolt between the 
tailboom and the NAS1587 countersunk washer. A minimum of two 
threads must extend past the nut plate.
    (6) Modify both access covers in accordance with the 
Accomplishment Instructions, paragraph 2.B.(6), of the SB600N-036.
    (b) Within 5 hours TIS, unless accomplished previously:
    (1) Drill four additional inspection holes in the fuselage as 
shown for the left side of the fuselage in Figure 1 of SB600N-039, 
by following the Accomplishment Instruction paragraphs of SB600N-039 
as follows:
    (i) Paragraphs 2.A.(1)(a), (b), and (d) for inspection holes at 
L166 and R166.
    (ii) Paragraphs 2.A.(2)(a), (b), and (d) for inspection holes at 
L153 and R153.
    (2) Thoroughly clean the attachment fittings and surrounding 
area. If the attachment fittings and surrounding area cannot be 
satisfactorily cleaned to accomplish a borescope inspection, then 
accomplish the actions in paragraph (c) of this AD.
    (3) Using a lighted borescope, inspect all four attachment 
fittings and the surrounding area for cracking.
    (i) If a crack is found in the upper right attachment fitting, 
accomplish the actions in paragraph (c) of this AD.
    (ii) If a crack is found in any of the other three attachment 
fittings, before further flight, accomplish the actions described in 
paragraph (f) of this AD.
    (4) Visually inspect the upper longerons for cracking in 
accordance with the Accomplishment Instructions, paragraph 2.C., of 
SB600N-039. If a crack is found in the upper longeron, accomplish 
the actions in paragraph (e) of this AD.

    Note 3: The reference in Figure 1 of SB600N-039 to the 
inspection hole at L167 mistakenly states that it was ``Added by 
SB900-036.'' Inspection holes at L167 and R167 were originally 
specified by SB600N-036.

    (c) Within 25 hours TIS, unless accomplished previously:
    (1) Thoroughly clean all attachment fittings and the surrounding 
areas, inspect the area for cracking, replace the upper right 
attachment fitting and all four nut plates, and paint the area 
inside of the attachment fittings in accordance with the 
Accomplishment Instructions, paragraph 2.B., of MD Helicopters 
Service Bulletin SB600N-043, dated April 13, 2006 (SB600N-043). If a 
crack is found in any of the other three attachment fittings, before 
further flight, accomplish the actions described in paragraph (f) of 
this AD.
    (2) Using a 10x magnifying glass, inspect the attachment bolts' 
threads and shanks for wear or damage in accordance with paragraph 
2.B., of SB600N-043. If wear or damage is present, replace the 
attachment bolts with airworthy bolts.
    (d) Thereafter, at the specified intervals, remove the plug 
buttons from the inspection holes, and using a bright light, inspect 
the upper and lower left and upper and lower right attachment 
fittings, angles, and nut plates for a crack by following the 
Accomplishment Instruction paragraphs of SB600N-039, as follows, 
except you are not required to contact MDHI to meet the requirements 
of this AD.
    (1) At intervals not to exceed 25 hours TIS, through inspection 
holes at L167 and R167, inspect the upper left and upper right 
attachment fittings, angles, and nut plates by following the 
Accomplishment Instructions, paragraphs 2.B.(2) through 2.B.(4), of 
SB600N-039.
    (2) At intervals not to exceed 100 hours TIS, through inspection 
holes at L166 and R166, inspect the lower left and lower right 
attachment fittings, angles, and nut plates by following the 
Accomplishment Instructions, paragraphs 2.B.(2) through 2.B.(4), of 
SB600N-039.
    (e) If a crack is found in the upper right attachment fitting, 
or in any angle, nut plate, longeron, or if thread wear or damage is 
found on any nut plate or bolt, before further flight, replace the 
cracked or worn or damaged part with an appropriate airworthy part, 
or accomplish the actions in paragraph (f) of this AD. If cracking 
is found in any of the other three attachment fittings, before 
further flight, accomplish the actions described in paragraph (f) of 
this AD.
    (f) If required by paragraph (c)(1) of this AD, or if you choose 
to make this modification to comply with paragraph (e) of this AD, 
modify the aft fuselage to strengthen the tailboom attachments and 
the longerons by following the Accomplishment Instructions of MD 
Helicopters Technical Bulletin TB600N-007, Revision 1, dated April 
13, 2006. Modifying the aft fuselage in accordance with this 
paragraph constitutes a terminating action for the requirements of 
this AD.
    (g) 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, 
Airframe Branch, FAA, ATTN: Jon Mowery, Aviation Safety Engineer, 
3960 Paramount Blvd., Lakewood, California 90712, telephone (562) 
627-5322, fax (562) 627-5210, for information about previously 
approved alternative methods of compliance.
    (h) Special flight permits may be issued in accordance with 14 
CFR 21.197 and 21.199 to operate the helicopter to the nearest 
maintenance facility capable of performing the inspections and 
modification.
    (i) The inspections shall be done in accordance with MD 
Helicopters Service Bulletin SB600N-036, dated November 2, 2001. The 
incorporation by reference of that document was approved previously 
by the Director of the Federal Register, in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51, as of April 29, 2002 (67 FR 17934, April 
12, 2002). The inspections, replacements and modifications shall be 
done in accordance with MD Helicopters Service Bulletin SB600N-039, 
dated December 9, 2003; MD Helicopters Service Bulletin SB600N-043, 
dated April 13, 2006; and MD Helicopters Technical Bulletin

[[Page 24812]]

TB600N-007, Revision 1, dated April 13, 2006. The incorporation by 
reference of these documents was approved by the Director of the 
Federal Register 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 web at www.mdhelicopters.com. Copies may be inspected 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.
    (j) This amendment becomes effective on April 27, 2006.

    Issued in Fort Worth, Texas, on April 20, 2006.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 06-3986 Filed 4-26-06; 8:45 am]
BILLING CODE 4910-13-P
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