Airworthiness Directives; Eurocopter France Model EC 155B, EC155B1, SA-360C, SA-365C, SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 Helicopters, 7382-7384 [05-2585]

Download as PDF 7382 Federal Register / Vol. 70, No. 29 / Monday, February 14, 2005 / Rules and Regulations 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 Note: The subject of this AD is addressed in Direction Generale de L’Aviation Civile (France) AD Nos. F–2004–033 and F–2004– 034, both dated March 17, 2004. Issued in Fort Worth, Texas, on January 25, 2005. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05–2587 Filed 2–11–05; 8:45 am] BILLING CODE 4910–13–P Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 DEPARTMENT OF TRANSPORTATION [Amended] 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: I 2005–03–08 Eurocopter France: Amendment 39–13964. Docket No. FAA–2004–19038; Directorate Identifier 2004–SW–24–AD. Applicability: Model AS350B, BA, B1, B2, B3, C, D, D1, and EC130 B4 helicopters, preMOD 073239, with fuel bleed lever, part number (P/N) 350A55104320, installed, certificated in any category. Compliance: Required within 6 months for the Model EC130 B4 helicopters and within 100 hours time-in-service or 6 months, whichever comes first, for the Model AS350B, BA, B1, B2, B3, C, D, and D1 helicopters, unless accomplished previously. To prevent a fuel bleed lever from separating and striking the tail rotor blade (blade), resulting in damage to or loss of a blade, and subsequent vibration and loss of control of the helicopter, do the following: (a) Remove and modify the fuel bleed lever, P/N 350A55104320, by following the Accomplishment Instructions, paragraph 2.B., of Eurocopter Alert Service Bulletin Nos. 28A001 for the Model EC130 B4 and 28.00.16 for the Model AS350B, BA, B1, B2, B3, C, D, and D1 helicopters, both dated March 3, 2004, as applicable. Reinstall the modified fuel bleed lever and mark it with P/N 350A08254720. (b) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group, FAA, for information about previously approved alternative methods of compliance. (c) The modification shall be done in accordance with Eurocopter Alert Service Bulletin Nos. 28A001 and 28.00.16, both dated March 3, 2004. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. 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. (d) This amendment becomes effective on March 21, 2005. VerDate jul<14>2003 15:21 Feb 11, 2005 Jkt 205001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20294; Directorate Identifier 2004–SW–39–AD; Amendment 39– 13965; AD 2005–03–09] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Model EC 155B, EC155B1, SA– 360C, SA–365C, SA–365C1, SA–365C2, SA–365N, SA–365N1, AS–365N2, AS 365 N3, and SA–366G1 Helicopters Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. AGENCY: SUMMARY: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters. This action requires an initial and repetitive borescope inspection of the main gearbox (MGB) planet gear carrier or an initial and repetitive visual inspection of the MGB planet gear carrier for a crack. Replacing any MGB that has a cracked planet gear carrier is required before further flight. This amendment is prompted by the discovery of cracks in the web of the planet gear carrier. The actions specified in this AD are intended to detect a crack in the web of the planet gear carrier, which could lead to a MGB seizure and subsequent loss of control of the helicopter. DATES: Effective March 1, 2005. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of March 1, 2005. Comments for inclusion in the Rules Docket must be received on or before April 15, 2005. 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 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 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. You may examine this information 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. 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: Uday Garadi, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193–0110, telephone (817) 222–5123, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for Eurocopter Model EC 155B, EC155B1, SA–360C, SA–365C, SA–365C1, SA– 365C2, SA–365N, SA–365N1, AS– 365N2, AS 365 N3, and SA–366G1. This action requires an initial and repetitive borescope inspection of the MGB planet gear carrier or an initial and repetitive visual inspection of the MGB planet gear carrier for a crack. Replacing any MGB that has a cracked planet gear carrier is required before further flight. This amendment is prompted by the discovery of cracks in the web of the E:\FR\FM\14FER1.SGM 14FER1 Federal Register / Vol. 70, No. 29 / Monday, February 14, 2005 / Rules and Regulations planet gear carrier. This condition, if not detected and corrected, could lead to a MGB seizure and subsequent loss of control of the helicopter. This AD is an interim action; the manufacturer and the FAA are continuing to collect information concerning the formation of these cracks. We will consider further rulemaking once we determine the cause of these cracks. The Direction Generale de L’Aviation Civile (DGAC), the airworthiness authority for France, notified the FAA that an unsafe condition may exist on Eurocopter Model EC 155B, EC155B1, SA 365 N and N1, AS 365 N2 and N3, SA 366 G1, SA 365 C, C1, C2, and C3, SA 360 helicopters. The DGAC advises of cases of cracks that were discovered in the web of the planet gear carrier of the MGB. The DGAC advises that rupture of the web of the planet gear carrier can lead to seizure of the MGB. Eurocopter has issued Alert Telex Nos. 05.00.48, 05.33, 05.26, and 05A007, dated December 16, 2004. The alert telex specifies performing periodic borescope inspections of the MGB planet gear carrier at regular intervals to make sure that there is no crack in the web. The manufacturer states that a periodic borescope inspection is mandatory, so that a crack, if any, can be detected before it generates any chips which can be found on the magnetic plug. The DGAC classified this alert telex as mandatory and issued AD UF– 2004–194, effective December 17, 2004, 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 these type designs 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 designs. Therefore, this AD is being issued to detect a crack in the web of the planet gear carrier, which could lead to a MGB seizure and subsequent loss of control of the helicopter. This AD requires the following: • For a MGB that has less than 250 hours time-in-service (TIS) since new or last overhaul, borescope inspecting or visually inspecting the web of the planet gear carrier for a crack. The inspections VerDate jul<14>2003 15:21 Feb 11, 2005 Jkt 205001 must be done on or before the MGB reaches 265 hours TIS and then at intervals not to exceed 50 hours TIS. • For a MGB that has 250 or more hours TIS since new or since last overhaul, borescope inspecting or visually inspecting the web of the planet gear carrier for a crack. The inspections must be done within 15 hours TIS and then at intervals not to exceed 50 hours TIS. • For any MGB that has a cracked planet gear carrier, replacing the MGB with an airworthy MGB before further flight. The inspections shall be done using the Alert Telex described previously. The short compliance time involved is required because the previously described critical unsafe condition can adversely affect the structural integrity and controllability of the helicopter. Fifty hours TIS equates to approximately 30 days of operations for these model helicopters. Therefore, because of the short compliance time, 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. We estimate that this AD will affect 145 helicopters. Each borescope inspection will take approximately 1 work hour and each visual inspection will take approximately 12 hours. Replacing the MGB, if necessary, will take approximately 16 work hours. The average labor rate is $65 per work hour. Required parts will cost approximately $68,780 per main gearbox. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $3,534,280, assuming that a borescope inspection is done on the entire fleet 12 times a year, that no visual inspection is done, and that 49 MGBs are replaced. 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 or deliver your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–20294; Directorate Identifier 2004–SW–39–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 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 7383 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 The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. 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. This rulemaking is promulgated under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, the FAA is charged 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 AD. E:\FR\FM\14FER1.SGM 14FER1 7384 Federal Register / Vol. 70, No. 29 / Monday, February 14, 2005 / Rules and Regulations List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Adoption of the Amendment Authority: 49 U.S.C. 106(g), 40113, 44701. 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 § 39.13 [Amended] 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: I 2005–03–09 Eurocopter France: Amendment 39–13965. Docket No. FAA–2005–20294; Directorate Identifier 2004–SW–39–AD. Applicability: Model EC 155B, EC155B1, SA–360C, SA–365C, SA–365C1, SA–365C2, SA–365N, SA–365N1, AS–365N2, AS 365 N3, and SA–366G1 helicopters, certificated in any category. Compliance: Required as indicated in the following table, unless accomplished previously. For a main gearbox (MGB) that has: Inspect: (1) Less than 250 hours time-in-service (TIS) since new or last overhaul. (2) 250 or more hours TIS since new or last overhaul ............................ On or before the MGB reaches 265 hours TIS and then at intervals not to exceed 50 hours TIS. Within 15 hours TIS and then at intervals not to exceed 50 hours TIS. To detect a crack in the web of the planet gear carrier, which could lead to a main gearbox (MGB) seizure and subsequent loss of control of the helicopter, accomplish the following: (a) Either borescope inspect the web of the MGB planet gear carrier for a crack in accordance with the Operational Procedure, paragraph 2.B.1., of Eurocopter Alert Telex No. 05.00.48, 05.33, 05.26, and 05A007, dated December 16, 2004 (Alert Telex) or visually inspect the MGB planet gear carrier in accordance with the Operational Procedure, paragraph 2.B.3., of the Alert Telex. (b) If a crack is found in the planet gear carrier, replace the MGB with an airworthy MGB before further flight. (c) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. (d) The inspections shall be done in accordance with Eurocopter Alert Telex No. 05.00.48, 05.33, 05.26, and 05A007, dated December 16, 2004. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. 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. (e) This amendment becomes effective on March 1, 2005. Note: The subject of this AD is addressed in Direction Generale de L’Aviation Civile (France) AD No. UF–2004–194, effective December 17, 2004. VerDate jul<14>2003 15:21 Feb 11, 2005 Jkt 205001 Issued in Fort Worth, Texas, on February 1, 2005. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05–2585 Filed 2–11–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2003–NM–16–AD; Amendment 39–13970; AD 2005–03–14] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: This amendment supersedes an existing airworthiness directive (AD) that applies to all Airbus Model A300 B2 and B4 series airplanes. The existing AD currently requires determining the part and amendment number of the variable lever arm (VLA) of the rudder control system to verify the parts were installed using the correct standard, and corrective actions if necessary. For certain VLAs, this new AD requires repetitive inspections of the VLA and corrective action if necessary. This new AD also provides a terminating action for the repetitive inspections. Furthermore, this new AD reduces the applicability of affected airplanes. The actions specified by this AD are intended to prevent failure of both spring boxes of certain VLAs due to corrosion damage, which could result in loss of rudder control and consequent reduced controllability of the airplane. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 This action is intended to address the identified unsafe condition. DATES: Effective March 21, 2005. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of March 21, 2005. The incorporation by reference of a certain other publication as listed in the regulations was approved previously by the Director of the Federal Register as of November 13, 2001 (66 FR 54416, October 29, 2001). ADDRESSES: The service information referenced in this AD may be obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; 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. Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: The FAA proposed to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) with an AD to supersede AD 2001–22–02, amendment 39–12481 (66 FR 54416, October 29, 2001). The existing AD applies to all Airbus Model A300 B2 and B4 series airplanes. The proposed AD was published as a supplemental notice of proposed FOR FURTHER INFORMATION CONTACT: E:\FR\FM\14FER1.SGM 14FER1

Agencies

[Federal Register Volume 70, Number 29 (Monday, February 14, 2005)]
[Rules and Regulations]
[Pages 7382-7384]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-2585]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20294; Directorate Identifier 2004-SW-39-AD; 
Amendment 39-13965; AD 2005-03-09]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model EC 155B, 
EC155B1, SA-360C, SA-365C, SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-
365N2, AS 365 N3, and SA-366G1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
the specified Eurocopter France (Eurocopter) model helicopters. This 
action requires an initial and repetitive borescope inspection of the 
main gearbox (MGB) planet gear carrier or an initial and repetitive 
visual inspection of the MGB planet gear carrier for a crack. Replacing 
any MGB that has a cracked planet gear carrier is required before 
further flight. This amendment is prompted by the discovery of cracks 
in the web of the planet gear carrier. The actions specified in this AD 
are intended to detect a crack in the web of the planet gear carrier, 
which could lead to a MGB seizure and subsequent loss of control of the 
helicopter.

DATES: Effective March 1, 2005.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 1, 2005.
    Comments for inclusion in the Rules Docket must be received on or 
before April 15, 2005.

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. You may 
examine this information 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.

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: Uday Garadi, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort 
Worth, Texas 76193-0110, telephone (817) 222-5123, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for 
Eurocopter Model EC 155B, EC155B1, SA-360C, SA-365C, SA-365C1, SA-
365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1. This 
action requires an initial and repetitive borescope inspection of the 
MGB planet gear carrier or an initial and repetitive visual inspection 
of the MGB planet gear carrier for a crack. Replacing any MGB that has 
a cracked planet gear carrier is required before further flight. This 
amendment is prompted by the discovery of cracks in the web of the

[[Page 7383]]

planet gear carrier. This condition, if not detected and corrected, 
could lead to a MGB seizure and subsequent loss of control of the 
helicopter.
    This AD is an interim action; the manufacturer and the FAA are 
continuing to collect information concerning the formation of these 
cracks. We will consider further rulemaking once we determine the cause 
of these cracks.
    The Direction Generale de L'Aviation Civile (DGAC), the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on Eurocopter Model EC 155B, EC155B1, SA 365 N and 
N1, AS 365 N2 and N3, SA 366 G1, SA 365 C, C1, C2, and C3, SA 360 
helicopters. The DGAC advises of cases of cracks that were discovered 
in the web of the planet gear carrier of the MGB. The DGAC advises that 
rupture of the web of the planet gear carrier can lead to seizure of 
the MGB.
    Eurocopter has issued Alert Telex Nos. 05.00.48, 05.33, 05.26, and 
05A007, dated December 16, 2004. The alert telex specifies performing 
periodic borescope inspections of the MGB planet gear carrier at 
regular intervals to make sure that there is no crack in the web. The 
manufacturer states that a periodic borescope inspection is mandatory, 
so that a crack, if any, can be detected before it generates any chips 
which can be found on the magnetic plug. The DGAC classified this alert 
telex as mandatory and issued AD UF-2004-194, effective December 17, 
2004, 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 these type designs 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 designs. Therefore, this AD is being 
issued to detect a crack in the web of the planet gear carrier, which 
could lead to a MGB seizure and subsequent loss of control of the 
helicopter. This AD requires the following:
     For a MGB that has less than 250 hours time-in-service 
(TIS) since new or last overhaul, borescope inspecting or visually 
inspecting the web of the planet gear carrier for a crack. The 
inspections must be done on or before the MGB reaches 265 hours TIS and 
then at intervals not to exceed 50 hours TIS.
     For a MGB that has 250 or more hours TIS since new or 
since last overhaul, borescope inspecting or visually inspecting the 
web of the planet gear carrier for a crack. The inspections must be 
done within 15 hours TIS and then at intervals not to exceed 50 hours 
TIS.
     For any MGB that has a cracked planet gear carrier, 
replacing the MGB with an airworthy MGB before further flight.
    The inspections shall be done using the Alert Telex described 
previously. The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
structural integrity and controllability of the helicopter. Fifty hours 
TIS equates to approximately 30 days of operations for these model 
helicopters. Therefore, because of the short compliance time, 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.
    We estimate that this AD will affect 145 helicopters. Each 
borescope inspection will take approximately 1 work hour and each 
visual inspection will take approximately 12 hours. Replacing the MGB, 
if necessary, will take approximately 16 work hours. The average labor 
rate is $65 per work hour. Required parts will cost approximately 
$68,780 per main gearbox. Based on these figures, the total cost impact 
of the AD on U.S. operators is estimated to be $3,534,280, assuming 
that a borescope inspection is done on the entire fleet 12 times a 
year, that no visual inspection is done, and that 49 MGBs are replaced.

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 or deliver your comments to 
an address listed under ADDRESSES. Include ``Docket No. FAA-2005-20294; 
Directorate Identifier 2004-SW-39-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

    The FAA's authority to issue rules regarding aviation safety is 
found in Title 49 of the United States Code. 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.
    This rulemaking is promulgated under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, the FAA is charged 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 AD.

[[Page 7384]]

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

2005-03-09 Eurocopter France: Amendment 39-13965. Docket No. FAA-
2005-20294; Directorate Identifier 2004-SW-39-AD.

    Applicability: Model EC 155B, EC155B1, SA-360C, SA-365C, SA-
365C1, SA-365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-
366G1 helicopters, certificated in any category.
    Compliance: Required as indicated in the following table, unless 
accomplished previously.

------------------------------------------------------------------------
   For a main gearbox (MGB) that has:                Inspect:
------------------------------------------------------------------------
(1) Less than 250 hours time-in-service  On or before the MGB reaches
 (TIS) since new or last overhaul.        265 hours TIS and then at
                                          intervals not to exceed 50
                                          hours TIS.
(2) 250 or more hours TIS since new or   Within 15 hours TIS and then at
 last overhaul.                           intervals not to exceed 50
                                          hours TIS.
------------------------------------------------------------------------

    To detect a crack in the web of the planet gear carrier, which 
could lead to a main gearbox (MGB) seizure and subsequent loss of 
control of the helicopter, accomplish the following:
    (a) Either borescope inspect the web of the MGB planet gear 
carrier for a crack in accordance with the Operational Procedure, 
paragraph 2.B.1., of Eurocopter Alert Telex No. 05.00.48, 05.33, 
05.26, and 05A007, dated December 16, 2004 (Alert Telex) or visually 
inspect the MGB planet gear carrier in accordance with the 
Operational Procedure, paragraph 2.B.3., of the Alert Telex.
    (b) If a crack is found in the planet gear carrier, replace the 
MGB with an airworthy MGB before further flight.
    (c) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Safety Management Group, Rotorcraft Directorate, FAA, 
for information about previously approved alternative methods of 
compliance.
    (d) The inspections shall be done in accordance with Eurocopter 
Alert Telex No. 05.00.48, 05.33, 05.26, and 05A007, dated December 
16, 2004. The Director of the Federal Register approved this 
incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 
CFR part 51. Copies may be obtained from American Eurocopter 
Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, 
telephone (972) 641-3460, fax (972) 641-3527. 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.
    (e) This amendment becomes effective on March 1, 2005.

    Note: The subject of this AD is addressed in Direction Generale 
de L'Aviation Civile (France) AD No. UF-2004-194, effective December 
17, 2004.


    Issued in Fort Worth, Texas, on February 1, 2005.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-2585 Filed 2-11-05; 8:45 am]
BILLING CODE 4910-13-P
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