Airworthiness Directives; Eurocopter France Model SA-360C, SA-365C, SA-365C1, and SA-365C2 Helicopters, 19110-19114 [06-3535]

Download as PDF 19110 Federal Register / Vol. 71, No. 71 / Thursday, April 13, 2006 / Rules and Regulations 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. Applicability Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. Unsafe Condition List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I HSRObinson on PROD1PC61 with RULES (d) This AD results from a report that certain structural provisions for an optional antenna are of insufficient strength. We are issuing this AD to prevent reduced structural integrity of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Installation (f) Within 24 months or 3,000 flight cycles after the effective date of this AD, whichever occurs first: Reinforce the fuselage at the emergency locator transmitter system’s antenna area in accordance with Part 1 or Part 2 of the Accomplishment Instructions of Fokker Service Bulletin SBF100–53–100, dated February 28, 2005, including Drawing W98488, Sheets 07 and 08, Issue F, dated February 9, 2004, and Sheets 09 and 10, Issue F, dated February 10, 2004. Alternative Methods of Compliance (AMOCs) (g)(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) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (h) Dutch airworthiness directive NL– 2005–004, dated April 29, 2005, also addresses the subject of this AD. PART 39—AIRWORTHINESS DIRECTIVES § 39.13 (c) This AD applies to Fokker Model F.28 Mark 0100 airplanes, certificated in any category; serial numbers 11290, 11296, 11323, 11329, and 11330, if modified in accordance with Fokker Service Bulletin SBF100–25–038 or SBF100–25–096. Material Incorporated by Reference (i) You must use Fokker Service Bulletin SBF100–53–100, dated February 28, 2005, including Drawing W98488, Sheets 07 and 08, Issue F, dated February 9, 2004, and Sheets 09 and 10, Issue F, dated February 10, 2004, to perform the actions that are required by this AD, unless the AD specifies otherwise. Fokker Service Bulletin SBF100– 53–100 contains the following effective pages: 2006–08–05 Fokker Services B.V.: Amendment 39–14559. Docket No. FAA–2006–24429; Directorate Identifier 2006–NM–003–AD. Effective Date (a) This AD becomes effective April 28, 2006. Affected ADs (b) None. VerDate Aug<31>2005 Page No. Revision level shown on page Date shown on page 1–9 ............... Original ........ February 28, 2005. Drawing W98488 07, 08 ........... 14:13 Apr 12, 2006 Jkt 208001 PO 00000 Frm 00014 F ................... Fmt 4700 February 9, 2004. Sfmt 4700 Page No. Revision level shown on page Date shown on page 09, 10 ........... F ................... February 10, 2004. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Fokker Services B.V., P.O. Box 231, 2150 AE NieuwVennep, the Netherlands, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at https:// dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on April 4, 2006. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–3480 Filed 4–12–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24446; Directorate Identifier 2005–SW–15–AD; Amendment 39– 14561; AD 2006–08–06] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Model SA–360C, SA–365C, SA– 365C1, and SA–365C2 Helicopters Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. AGENCY: SUMMARY: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model SA–360C, SA–365C, SA–365C1, and SA–365C2 helicopters. This action requires inspecting the main gearbox (MGB) base plate for a crack and replacing the MGB if a crack is found. This amendment is prompted by the discovery of a crack in a MGB base plate. The actions specified in this AD are intended to detect a crack in a MGB base plate and prevent failure of one of the MGB attachment points to the frame, which could result in severe vibration and subsequent loss of control of the helicopter. DATES: Effective April 28, 2006. E:\FR\FM\13APR1.SGM 13APR1 Federal Register / Vol. 71, No. 71 / Thursday, April 13, 2006 / Rules and Regulations Comments for inclusion in the Rules Docket must be received on or before June 12, 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 American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. 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: Ed Cuevas, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5355, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for Eurocopter Model SA–360C, SA–365C, SA–365C1, and SA–365C2 helicopters with an MGB base plate, part number (P/N) 360A32–2311–02 or P/N 360A32– 2311–03. This action requires visually inspecting the MGB for a crack in the MGB base plate, close to the attachment hole, using a 10x or higher magnifying glass. Stripping paint from the inspection area is also required, but only before the initial inspection. This amendment is prompted by the discovery of a crack in the MGB base plate of a MGB installed in a Eurocopter Model AS–365 N2 helicopter, which is of similar type design to the helicopter models affected by this AD. The cause of the crack is under investigation; therefore, this AD is an interim action until the cause of the crack can be determined. The crack was located very close to the attachment points of one of the laminated pads, and it propagated to the inside of the MGB base plate and then continued into the MGB casing. This condition, if not detected, could result in failure of one of the MGB attachment points to the frame, which could result in severe vibration and subsequent loss of control of the helicopter. We have previously issued AD 2004– 16–15, Amendment 39–13771 (69 FR 51358), that applies to Eurocopter Model AS–365N2, AS 365 N3, EC 155B, EC155B1, SA–365N and N1, and SA– 366G1 helicopters with an MGB base plate, P/N 366A32–1062–03 or P/N 366A32–1062–06. Since the issuance of ´ ´ that AD, the Direction Generale de L’Aviation Civile (DGAC), the airworthiness authority for France, notified us that an unsafe condition may also exist on Eurocopter Model SA 360 C and SA 365 C, C1, C2, and C3 helicopters. The SA 365 C3 is not type certificated in the United States. The DGAC advises of the discovery of a crack on the MGB base plate of a Model AS 365 N2 helicopter. Eurocopter has issued Alert Service Bulletin No. 05.25, dated February 17, 2005 (ASB), which specifies visually inspecting the MGB base plate for the absence of cracks. In addition, the ASB 19111 states that a 10x magnifying glass can be used to facilitate the crack inspection. If in doubt about the existence of a crack, the ASB specifies inspecting for a crack using a dye-penetrant crack detection inspection. The ASB also states that after the crack was discovered on the Eurocopter Model AS365 N2 helicopter, the Eurocopter Model SA360 C and SA365C, C1, C2, and C3 helicopters were excluded from monitoring requirements. However, after issuing an Alert Telex, further cases of cracks were reported on helicopters covered by the monitoring requirement. Also, since the issuance of their initial service information, additional investigations and examinations have shown that the helicopter versions initially excluded from the monitoring requirements are also concerned by the potential risk and their MGB bottom plate must also be monitored. The DGAC classified this ASB as mandatory and issued AD No. F–2005–036, dated March 2, 2005, to ensure the continued airworthiness of these helicopters in France. These helicopter models are manufactured in France and are type certificated for operation in the United States under the provisions of 14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the applicable bilateral agreement, the DGAC has kept the FAA informed of the situation described above. The FAA has examined the findings of the DGAC, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. This unsafe condition is likely to exist or develop on other helicopters of the same type design. Therefore, this AD is being issued to detect a crack in the MGB base plate and prevent failure of a MGB attachment point to the frame, which could result in severe vibration and subsequent loss of control of the helicopter. This AD requires initial and repetitive inspections of the MGB base plate for cracking at the following intervals: HSRObinson on PROD1PC61 with RULES For any MGB that: Accomplish the AD actions: (a) Has less than 26,900 cycles and has never been overhauled or repaired. (b) Has 26,900 or more cycles and has never been overhauled or repaired. (c) Is installed that has been overhauled or repaired .............................. On or before accumulating 26,900 cycles and thereafter at intervals not to exceed 55 hours time-in-service (TIS). Before further flight and thereafter at intervals not to exceed 55 hours TIS. Before further flight and thereafter at intervals not to exceed 55 hours TIS. One cycle equates to one helicopter landing in which a landing gear touches the ground. VerDate Aug<31>2005 14:13 Apr 12, 2006 Jkt 208001 PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 E:\FR\FM\13APR1.SGM 13APR1 19112 Federal Register / Vol. 71, No. 71 / Thursday, April 13, 2006 / Rules and Regulations None of the Eurocopter Model SA– 360C, SA–365C, SA–365C1, and SA– 365C2 helicopters affected by this action are on the U.S. Register. All helicopters included in the applicability of this rule are currently operated by non-U.S. operators under foreign registry; therefore, they are not directly affected by this AD action. However, the FAA considers that this rule is necessary to ensure that the unsafe condition is addressed in the event that any of these subject helicopters are imported and placed on the U.S. Register in the future. Should an affected helicopter be imported and placed on the U.S. Register in the future, it would take approximately 0.5 work hour for the initial inspection and 0.25 work hour for each recurring inspection. Replacing the MGB, if necessary, would take approximately 4 work hours to accomplish, at an average labor rate of $65 per work hour. It would cost approximately $25,000 to repair a cracked MGB base plate. Based on these figures, the cost impact of this AD would be $25,455, assuming that one helicopter is imported and inspected 11 times (the initial inspection plus 10 recurring inspections) and the MGB is replaced once. Since this AD action does not affect any helicopter that is currently on the U.S. register, it has no adverse economic impact and imposes no additional burden on any person. Therefore, notice and public procedures hereon are unnecessary and the amendment may be made effective in less than 30 days after publication in the Federal Register. Comments Invited This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–200X– XXXXX; Directorate Identifier 2005– SW–15–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 notice and prior public comment are unnecessary in promulgating this regulation; therefore, it can be issued immediately to correct an unsafe condition in aircraft since none of these model helicopters are registered in the United States. We have also determined that this regulation is not a ‘‘significant regulatory action’’ under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the AD docket. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: I 2006–08–06 Eurocopter France: Amendment 39–14561. Docket No. FAA–2006–24446; Directorate Identifier 2005–SW–15–AD. Applicability Model SA–360C, SA–365C, SA–365C1, and SA–365C2 helicopters with a main gearbox (MGB) base plate, part number (P/N) 360A32–2311–02 or P/N 360A32–2311–03 installed, certificated in any category. Compliance Required as indicated in the following compliance table, unless accomplished previously, and before installing a replacement main gearbox (MGB). COMPLIANCE TABLE HSRObinson on PROD1PC61 with RULES For any MGB that: Accomplish the AD actions: (a) Has less than 26,900 cycles and has never been overhauled or repaired. (b) Has 26,900 or more cycles and has never been overhauled or repaired. (c) Is installed that has been overhauled or repaired .............................. On or before accumulating 26,900 cycles and thereafter at intervals not to exceed 55 hours time-in-service (TIS). Before further flight and thereafter at intervals not to exceed 55 hours TIS. Before further flight and thereafter at intervals not to exceed 55 hours TIS. One cycle equates to one helicopter landing in which a landing gear touches the ground. VerDate Aug<31>2005 14:13 Apr 12, 2006 Jkt 208001 PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 E:\FR\FM\13APR1.SGM 13APR1 Federal Register / Vol. 71, No. 71 / Thursday, April 13, 2006 / Rules and Regulations control of the helicopter, accomplish the following: (a) Before the initial inspection at the time indicated in the compliance table, strip the paint from area ‘‘D’’ on both sides (‘‘B’’ and ‘‘C’’) of the MGB base plate as depicted in Figure 1 of this AD. BILLING CODE 4910–13–P BILLING CODE 4910–13–C VerDate Aug<31>2005 14:13 Apr 12, 2006 Jkt 208001 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\13APR1.SGM 13APR1 ER13AP06.024</GPH> HSRObinson on PROD1PC61 with RULES To detect a crack in a MGB base plate and prevent failure of one of the MGB attachment points to the frame, which could result in severe vibration and subsequent loss of 19113 19114 Federal Register / Vol. 71, No. 71 / Thursday, April 13, 2006 / Rules and Regulations (b) At the times indicated in the compliance table, inspect area ‘‘D’’ of the MGB base plate for a crack using a 10x or higher magnifying glass. Area ‘‘D’’ to be inspected is depicted in Figure 1 of this AD. Note 1: Eurocopter France Alert Service Bulletin No. 05.25, dated February 17, 2005, pertain to the subject of this AD. (c) If a crack is found in a MGB base plate, remove and replace the MGB with an airworthy MGB before further flight. (d) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Safety Management Group, Rotorcraft Directorate, FAA, ATTN: Ed Cuevas, Fort Worth, Texas 76193–0111, telephone (817) 222–5355, fax (817) 222–5961, for information about previously approved alternative methods of compliance. (e) This amendment becomes effective on April 28, 2006. Note 2: The subject of this AD is addressed ´ ´ in Direction Generale de L’Aviation Civile (France) AD No. F–2005–036, dated March 2, 2005. Issued in Fort Worth, Texas, on April 5, 2006. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 06–3535 Filed 4–12–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24438; Directorate Identifier 2006–NM–061–AD; Amendment 39–14560; AD 2006–04–13 R1] RIN 2120–AA64 Airworthiness Directives; Gulfstream Model GIV–X and GV–SP Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is revising an existing airworthiness directive (AD), which applies to certain Gulfstream Model GIV–X and GV–SP series airplanes. That AD currently requires revising the Limitations section of the airplane flight manual (AFM) by incorporating new procedures to follow in the event that the cockpit displays go blank or malfunction. This AD allows for the use of alternative AFM revisions for a certain subset of the existing applicability. This AD results from a report that all four of the cockpit flight panel display units simultaneously went blank during flight. We are issuing this AD to ensure that the flightcrew is advised of the appropriate procedures to follow in the event that the cockpit displays go blank or malfunction, which could result in a reduction of the flightcrew’s situational awareness and possible loss of control of the airplane. DATES: The effective date of this AD is March 13, 2006. On March 13, 2006 (71 FR 9436, February 24, 2006), the Director of the Federal Register approved the incorporation by reference of certain other publications. We must receive any comments on this AD by June 12, 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. • 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. Contact Gulfstream Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, Savannah, Georgia 31402–2206, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Robert Chupka, Aerospace Engineer, Systems and Equipment Branch, ACE– 119A, Atlanta Aircraft Certification Office, FAA, One Crown Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 30349; telephone (770) 703– 6070; fax (770) 703–6097. SUPPLEMENTARY INFORMATION: Discussion On February 14, 2006, we issued AD 2006–04–13, amendment 39–14495 (71 FR 9436, February 24, 2006). That AD applies to certain Gulfstream Model GIV–X and GV–SP series airplanes. That AD requires revising the Limitations section of the airplane flight manual (AFM) by incorporating new procedures to follow in the event that the cockpit displays go blank or malfunction. That AD resulted from a report that all four of the cockpit flight panel display units simultaneously went blank during flight. The actions specified in that AD are intended to ensure that the flightcrew is advised of the appropriate procedures to follow in the event that the cockpit displays go blank or malfunction, which could result in a reduction of the flightcrew’s situational awareness and possible loss of control of the airplane. Actions Since AD Was Issued Since we issued AD 2006–04–13, the European Aviation Safety Agency (EASA) informed us that the information contained in the Joint Aviation Authority (JAA) Gulfstream AFM revisions is considered acceptable for airplanes operated under and in accordance with the JAA and EASA regulations, supervision, and oversight, and should be added to the AD. We inadvertently omitted that information from AD 2006–04–13; therefore, we have added a new Note 2 to this AD to give credit for those revisions. Relevant Service Information We have reviewed the revisions to the Limitations section of Gulfstream G350, G450, G500, and G550 AFMs, as listed in the table below: GULFSTREAM AFM REVISIONS Revision level HSRObinson on PROD1PC61 with RULES Affected airplane models AFM Model GIV–X ................................... Gulfstream G350 ...................................................................................... GAC–AC–JAA–G350–OPS–0001 Gulfstream G450 ...................................................................................... GAC–AC–JAA–G450–OPS–0001 Gulfstream G500 ...................................................................................... GAC–AC–JAA–G500–OPS–0001 Model GIV–X ................................... Model GV–SP ................................. VerDate Aug<31>2005 14:13 Apr 12, 2006 Jkt 208001 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 E:\FR\FM\13APR1.SGM 13APR1 Revision date 3 January 25, 2006. 3 January 25, 2006. 3 January 25, 2006.

Agencies

[Federal Register Volume 71, Number 71 (Thursday, April 13, 2006)]
[Rules and Regulations]
[Pages 19110-19114]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-3535]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24446; Directorate Identifier 2005-SW-15-AD; 
Amendment 39-14561; AD 2006-08-06]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA-360C, SA-
365C, SA-365C1, and SA-365C2 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
Eurocopter France (Eurocopter) Model SA-360C, SA-365C, SA-365C1, and 
SA-365C2 helicopters. This action requires inspecting the main gearbox 
(MGB) base plate for a crack and replacing the MGB if a crack is found. 
This amendment is prompted by the discovery of a crack in a MGB base 
plate. The actions specified in this AD are intended to detect a crack 
in a MGB base plate and prevent failure of one of the MGB attachment 
points to the frame, which could result in severe vibration and 
subsequent loss of control of the helicopter.

DATES: Effective April 28, 2006.

[[Page 19111]]

    Comments for inclusion in the Rules Docket must be received on or 
before June 12, 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 
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 
75053-4005, telephone (972) 641-3460, fax (972) 641-3527.

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: Ed Cuevas, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas 
76193-0111, telephone (817) 222-5355, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for 
Eurocopter Model SA-360C, SA-365C, SA-365C1, and SA-365C2 helicopters 
with an MGB base plate, part number (P/N) 360A32-2311-02 or P/N 360A32-
2311-03. This action requires visually inspecting the MGB for a crack 
in the MGB base plate, close to the attachment hole, using a 10x or 
higher magnifying glass. Stripping paint from the inspection area is 
also required, but only before the initial inspection. This amendment 
is prompted by the discovery of a crack in the MGB base plate of a MGB 
installed in a Eurocopter Model AS-365 N2 helicopter, which is of 
similar type design to the helicopter models affected by this AD. The 
cause of the crack is under investigation; therefore, this AD is an 
interim action until the cause of the crack can be determined. The 
crack was located very close to the attachment points of one of the 
laminated pads, and it propagated to the inside of the MGB base plate 
and then continued into the MGB casing. This condition, if not 
detected, could result in failure of one of the MGB attachment points 
to the frame, which could result in severe vibration and subsequent 
loss of control of the helicopter.
    We have previously issued AD 2004-16-15, Amendment 39-13771 (69 FR 
51358), that applies to Eurocopter Model AS-365N2, AS 365 N3, EC 155B, 
EC155B1, SA-365N and N1, and SA-366G1 helicopters with an MGB base 
plate, P/N 366A32-1062-03 or P/N 366A32-1062-06. Since the issuance of 
that AD, the Direction G[eacute]n[eacute]rale de L'Aviation Civile 
(DGAC), the airworthiness authority for France, notified us that an 
unsafe condition may also exist on Eurocopter Model SA 360 C and SA 365 
C, C1, C2, and C3 helicopters. The SA 365 C3 is not type certificated 
in the United States. The DGAC advises of the discovery of a crack on 
the MGB base plate of a Model AS 365 N2 helicopter.
    Eurocopter has issued Alert Service Bulletin No. 05.25, dated 
February 17, 2005 (ASB), which specifies visually inspecting the MGB 
base plate for the absence of cracks. In addition, the ASB states that 
a 10x magnifying glass can be used to facilitate the crack inspection. 
If in doubt about the existence of a crack, the ASB specifies 
inspecting for a crack using a dye-penetrant crack detection 
inspection. The ASB also states that after the crack was discovered on 
the Eurocopter Model AS365 N2 helicopter, the Eurocopter Model SA360 C 
and SA365C, C1, C2, and C3 helicopters were excluded from monitoring 
requirements. However, after issuing an Alert Telex, further cases of 
cracks were reported on helicopters covered by the monitoring 
requirement. Also, since the issuance of their initial service 
information, additional investigations and examinations have shown that 
the helicopter versions initially excluded from the monitoring 
requirements are also concerned by the potential risk and their MGB 
bottom plate must also be monitored. The DGAC classified this ASB as 
mandatory and issued AD No. F-2005-036, dated March 2, 2005, to ensure 
the continued airworthiness of these helicopters in France.
    These helicopter models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral agreement, the DGAC has kept the FAA informed of 
the situation described above. The FAA has examined the findings of the 
DGAC, reviewed all available information, and determined that AD action 
is necessary for products of this type design that are certificated for 
operation in the United States.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, this AD is being issued 
to detect a crack in the MGB base plate and prevent failure of a MGB 
attachment point to the frame, which could result in severe vibration 
and subsequent loss of control of the helicopter. This AD requires 
initial and repetitive inspections of the MGB base plate for cracking 
at the following intervals:

------------------------------------------------------------------------
           For any MGB that:                Accomplish the AD actions:
------------------------------------------------------------------------
(a) Has less than 26,900 cycles and has  On or before accumulating
 never been overhauled or repaired.       26,900 cycles and thereafter
                                          at intervals not to exceed 55
                                          hours time-in-service (TIS).
(b) Has 26,900 or more cycles and has    Before further flight and
 never been overhauled or repaired.       thereafter at intervals not to
                                          exceed 55 hours TIS.
(c) Is installed that has been           Before further flight and
 overhauled or repaired.                  thereafter at intervals not to
                                          exceed 55 hours TIS.
------------------------------------------------------------------------
One cycle equates to one helicopter landing in which a landing gear
 touches the ground.
------------------------------------------------------------------------


[[Page 19112]]

    None of the Eurocopter Model SA-360C, SA-365C, SA-365C1, and SA-
365C2 helicopters affected by this action are on the U.S. Register. All 
helicopters included in the applicability of this rule are currently 
operated by non-U.S. operators under foreign registry; therefore, they 
are not directly affected by this AD action. However, the FAA considers 
that this rule is necessary to ensure that the unsafe condition is 
addressed in the event that any of these subject helicopters are 
imported and placed on the U.S. Register in the future.
    Should an affected helicopter be imported and placed on the U.S. 
Register in the future, it would take approximately 0.5 work hour for 
the initial inspection and 0.25 work hour for each recurring 
inspection. Replacing the MGB, if necessary, would take approximately 4 
work hours to accomplish, at an average labor rate of $65 per work 
hour. It would cost approximately $25,000 to repair a cracked MGB base 
plate. Based on these figures, the cost impact of this AD would be 
$25,455, assuming that one helicopter is imported and inspected 11 
times (the initial inspection plus 10 recurring inspections) and the 
MGB is replaced once.
    Since this AD action does not affect any helicopter that is 
currently on the U.S. register, it has no adverse economic impact and 
imposes no additional burden on any person. Therefore, notice and 
public procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any written data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-200X-XXXXX; 
Directorate Identifier 2005-SW-15-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 notice and prior public comment are 
unnecessary in promulgating this regulation; therefore, it can be 
issued immediately to correct an unsafe condition in aircraft since 
none of these model helicopters are registered in the United States. We 
have also determined that this regulation is not a ``significant 
regulatory action'' under Executive Order 12866. It has been determined 
further that this action involves an emergency regulation under DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If 
it is determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the AD docket.

Authority for This Rulemaking

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

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

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

2006-08-06 Eurocopter France: Amendment 39-14561. Docket No. FAA-
2006-24446; Directorate Identifier 2005-SW-15-AD.

Applicability

    Model SA-360C, SA-365C, SA-365C1, and SA-365C2 helicopters with 
a main gearbox (MGB) base plate, part number (P/N) 360A32-2311-02 or 
P/N 360A32-2311-03 installed, certificated in any category.

Compliance

    Required as indicated in the following compliance table, unless 
accomplished previously, and before installing a replacement main 
gearbox (MGB).

                            Compliance Table
------------------------------------------------------------------------
           For any MGB that:                Accomplish the AD actions:
------------------------------------------------------------------------
(a) Has less than 26,900 cycles and has  On or before accumulating
 never been overhauled or repaired.       26,900 cycles and thereafter
                                          at intervals not to exceed 55
                                          hours time-in-service (TIS).
(b) Has 26,900 or more cycles and has    Before further flight and
 never been overhauled or repaired.       thereafter at intervals not to
                                          exceed 55 hours TIS.
(c) Is installed that has been           Before further flight and
 overhauled or repaired.                  thereafter at intervals not to
                                          exceed 55 hours TIS.
------------------------------------------------------------------------
One cycle equates to one helicopter landing in which a landing gear
 touches the ground.
------------------------------------------------------------------------


[[Page 19113]]

    To detect a crack in a MGB base plate and prevent failure of one 
of the MGB attachment points to the frame, which could result in 
severe vibration and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Before the initial inspection at the time indicated in the 
compliance table, strip the paint from area ``D'' on both sides 
(``B'' and ``C'') of the MGB base plate as depicted in Figure 1 of 
this AD.

BILLING CODE 4910-13-P
[GRAPHIC] [TIFF OMITTED] TR13AP06.024

BILLING CODE 4910-13-C

[[Page 19114]]

    (b) At the times indicated in the compliance table, inspect area 
``D'' of the MGB base plate for a crack using a 10x or higher 
magnifying glass. Area ``D'' to be inspected is depicted in Figure 1 
of this AD.


    Note 1: Eurocopter France Alert Service Bulletin No. 05.25, 
dated February 17, 2005, pertain to the subject of this AD.


    (c) If a crack is found in a MGB base plate, remove and replace 
the MGB with an airworthy MGB before further flight.
    (d) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Safety Management Group, Rotorcraft 
Directorate, FAA, ATTN: Ed Cuevas, Fort Worth, Texas 76193-0111, 
telephone (817) 222-5355, fax (817) 222-5961, for information about 
previously approved alternative methods of compliance.
    (e) This amendment becomes effective on April 28, 2006.


    Note 2: The subject of this AD is addressed in Direction 
G[eacute]n[eacute]rale de L'Aviation Civile (France) AD No. F-2005-
036, dated March 2, 2005.


    Issued in Fort Worth, Texas, on April 5, 2006.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 06-3535 Filed 4-12-06; 8:45 am]
BILLING CODE 4910-13-P

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