Airworthiness Directives; Eurocopter France (Eurocopter) Helicopters, 60188-60191 [2013-23580]

Download as PDF 60188 Federal Register / Vol. 78, No. 190 / Tuesday, October 1, 2013 / Rules and Regulations 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. Regulatory Findings We 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, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and 4. 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 and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. wreier-aviles on DSK5TPTVN1PROD with RULES Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. VerDate Mar<15>2010 14:43 Sep 30, 2013 Jkt 232001 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2013–15–01 AGUSTAWESTLAND S.p.A.: Amendment 39–17517; Docket No. FAA–2013–0640; Directorate Identifier 2013–SW–016–AD. (a) Applicability This AD applies to Model AB139 and AW139 helicopters with a Full Icing Protection System (FIPS) installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as improper insulation of an electrical cable resulting in failure of the FIPS Auto Transformer Rectifier Unit to contain the internal circuit overload. This condition could result in a fire, structural damage, and subsequent loss of control of the helicopter. Giovanni Cecchelli; telephone 39–0331– 711133; fax 39 0331 711180; or at http:// www.agustawestland.com/technicalbullettins. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2013–0124, dated June 5, 2013. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA–2013–0640. (i) Subject Joint Aircraft Service Component (JASC) Code: 3060 Ice Protection. Issued in Fort Worth, Texas, on July 11, 2013. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. (c) Effective Date This AD becomes effective October 16, 2013. [FR Doc. 2013–23578 Filed 9–30–13; 8:45 am] (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. DEPARTMENT OF TRANSPORTATION (e) Required Actions Before further flight, deactivate the FIPS, and install a placard with 6 millimeter red letters on a white background next to the FIPS controller that states the following: ‘‘FLIGHT INTO KNOWN ICING IS PROHIBITED.’’ (f) Special Flight Permits Special flight permits are prohibited. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Andy Shaw, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email andy.shaw@ faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (h) Additional Information (1) AgustaWestland Bollettino Tecnico (BT) No. 139–324, Revision A, dated June 4, 2013, and AgustaWestland BT No. 139–330, dated June 4, 2013, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact AgustaWestland, Customer Support & Services, Via Per Tornavento 15, 21019 Somma Lombardo (VA) Italy, ATTN: PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 BILLING CODE 4910–13–P Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0807; Directorate Identifier 2013–SW–035–AD; Amendment 39–17601; AD 2013–19–19] RIN 2120–AA64 Airworthiness Directives; Eurocopter France (Eurocopter) Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for Eurocopter Model AS332C, AS332L, AS332L1, AS332L2, and EC225LP helicopters. This AD requires replacing certain serial-numbered main gearbox (MGB) bevel gear vertical shafts because they are no longer airworthy. Also, this AD requires certain inspections of each MGB bevel gear vertical shaft (shaft) for a crack. Also, this AD requires if there is a crack, replacing the shaft with an airworthy part before further flight. This AD is prompted by two incidents of emergency ditching after warning indications of loss of MGB oil pressure. These actions are intended to detect a cracked shaft, which could result in loss of MGB oil pressure, loss of the MGB lubrication system, and subsequent loss of control of the helicopter. DATES: This AD becomes effective October 16, 2013. SUMMARY: E:\FR\FM\01OCR1.SGM 01OCR1 Federal Register / Vol. 78, No. 190 / Tuesday, October 1, 2013 / Rules and Regulations We must receive comments on this AD by December 2, 2013. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit them only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments. Examining the AD Docket Discussion We are adopting a new AD for the specified Eurocopter helicopters with certain part-numbered shafts. This AD requires replacing certain serialnumbered shafts because they are no longer airworthy. Also, this AD requires certain inspections at specified intervals of each shaft for a crack. This AD also requires if there is a crack, replacing the shaft with an airworthy part before further flight. This AD is prompted by two incidents of emergency ditching after warning indication of loss of oil pressure. A full circumferential crack of the lower shaft occurred in the area where two sections of the shaft are welded together. As a result, the shaft stopped driving the main and backup oil pumps leading to warning indications of the loss of the MGB lubrication. The crew activated the MGB emergency lubrication system, and following a warning that indicated failure of that system, performed a controlled ditching into the sea. These actions are intended to detect a cracked shaft, which could result in loss of MGB oil pressure, loss of the MGB lubrication system, and subsequent loss of control of the helicopter. This AD is prompted by EASA AD 2013–0138R1, dated July 15, 2013, issued by EASA, which is the Technical Agent for the Member States of the European Union. EASA AD 2013– 0138R1 was issued to revise EASA AD 2013–0138–E, dated July 9, 2013, which superseded EASA Emergency AD 2012– 1250–E, dated November 21, 2012, to correct an unsafe condition for the Eurocopter Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters, all serial numbers, with certain part-numbered shafts, installed. EASA advises of two events of the Model EC225LP helicopters. In both cases, an emergency ditching was You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the European Aviation Safety Agency (EASA) AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this AD, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http://www.euro copter.com/techpub. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. FOR FURTHER INFORMATION CONTACT: Rao Edupuganti, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email rao.edupuganti@faa.gov. SUPPLEMENTARY INFORMATION: wreier-aviles on DSK5TPTVN1PROD with RULES Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or VerDate Mar<15>2010 14:43 Sep 30, 2013 Jkt 232001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 60189 performed after warning indication of MGB loss of oil pressure and subsequent additional red alarm on the MGB emergency lubrication system (EMLUB). EASA also advises of a full circumferential crack of the lower vertical shaft of the MGB bevel gear in the area where the two sections of the shaft are welded together. As a result, the vertical shaft ceased to drive the main and backup oil pumps leading to warning indications of the loss of the MGB main and standby oil lubrication systems. The crew activated the EMLUB system and, following a subsequent warning indicating failure of that system, performed a controlled ditching into the sea. EASA advises that Eurocopter determined after investigating the incidents that the MGB bevel gear vertical shaft failures resulted from a combination of factors, including stress hot-spots induced by the shaft geometry, residual stresses in the shaft weld material resulting from the manufacturing process, and corrosion pitting inside the shaft on areas where gear spline wear particles accumulated. The EASA AD allows continued operations under certain conditions if equipped with a Vibration Health Monitoring System (VHM). FAA’s Determination These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs. Interim Action We consider this AD interim action. The design approval holder is currently developing a newly-designed shaft that will address the unsafe condition identified in this AD. Once the newlydesigned shaft is developed, approved, and available, we might consider additional rulemaking. Related Service Information Eurocopter has issued the following service information: • ASB No. AS332–01.00.82, Revision 3, dated July 8, 2013, for the Model AS332C, C1, L, L1, L2 civil helicopters and Model AS332B, B1, M, M1, and F1 military model helicopters. The ASB defines the new inspection E:\FR\FM\01OCR1.SGM 01OCR1 60190 Federal Register / Vol. 78, No. 190 / Tuesday, October 1, 2013 / Rules and Regulations requirements to detect a crack in the shaft. • ASB No. EC225–04A009, Revision 3, dated July 8, 2013 for Model EC225LP helicopters. The ASB defines the new inspection requirements to detect a crack in the shaft. AD Requirements This AD requires: • Removing certain part-numbered and serial-numbered shafts from service, which are no longer considered airworthy. • For certain model helicopters, before further flight and at specified intervals, eddy current inspecting the shaft for a crack in the area of the weld. • For Model EC225LP, before further flight, either installing a placard in full view of the pilot with the following statement in red, 6 millimeter letters on a white background: ‘‘MAXIMUM CONTINUOUS TORQUE LIMITED TO 70% DURING LEVEL FLIGHTS AT IAS EQUAL TO OR MORE THAN 60 KTS,’’ and before further flight and thereafter at intervals not to exceed 11.5 hours TIS, removing the main jet and emergency spraying jet, and ultrasonic inspecting the shaft in the weld area for a crack; or • Before further flight and thereafter at intervals not to exceed 8 hours TIS, removing the main jet and emergency spraying jet, and ultrasonic inspecting the shaft for a crack in the area of the weld. • Each eddy current or ultrasonic inspection be done by a Level II or Level III operator certified in the ultrasonic fault detection method in the Aeronautics Sector according to the EN4179 or NAS410 standard. • If there is a crack, before further flight, replacing the shaft with an airworthy part. Differences Between This AD and the EASA AD The EASA AD allows continued operations under certain conditions if equipped with a VHM. The VHM system is validated by FAA for information only, and therefore we have not adopted that portion of the EASA AD. wreier-aviles on DSK5TPTVN1PROD with RULES Costs of Compliance We estimate that this AD will affect four helicopters of U.S. Registry. We estimate that operators may incur the following costs to comply with this AD. We estimate labor at $85 per work hour. Minimal cost to install a placard and 3 work hours to inspect each shaft for a crack, it will cost $255 per helicopter and $1,020 for the fleet per inspection. To replace a shaft, it will VerDate Mar<15>2010 14:43 Sep 30, 2013 Jkt 232001 take 44 work hours and $1,243,350 for required parts for a total of $1,247,090 per helicopter. FAA’s Justification and Determination of the Effective Date Providing an opportunity for public comments before adopting these AD requirements would delay implementing the safety actions needed to correct this known unsafe condition. Therefore, we find that the risk to the flying public justifies waiving notice and comment before adopting this rule because the required corrective actions must be done within 10 hours TIS and at repeated intervals within short periods of time. Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in less than 30 days. 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. Regulatory Findings We 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, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and 4. 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 and placed it in the AD docket. 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: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2013–19–19 Eurocopter France: Amendment 39–17601; Docket No. FAA–2013–0807; Directorate Identifier 2013–SW–035–AD. (a) Applicability This AD applies to Eurocopter Model AS332C, AS332L, AS332L1, AS332L2, and EC225LP helicopters, with main gearbox (MGB) bevel gear vertical shaft (shaft), part number (P/N) 332A32–5101–00, 332A32– 5101–05, 332A32–5101–10, or 332A32– 5101–15, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a cracked shaft resulting in loss of MGB oil pressure. These actions are intended to prevent loss of the MGB lubrication system and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective October 16, 2013. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions (1) Before further flight, remove shaft, P/N 332A32–5101–00, 332A32–5101–05, 332A32–5101–10, or 332A32–5101–15, with S/N M330 through M340 (inclusive) and S/ N M370 through M5000 (inclusive) from service, which are no longer considered airworthy. E:\FR\FM\01OCR1.SGM 01OCR1 Federal Register / Vol. 78, No. 190 / Tuesday, October 1, 2013 / Rules and Regulations (2) For Model AS332C, AS332L, AS332L1, and AS332L2 helicopters, before further flight and thereafter at intervals not to exceed 10 hours time-in-service (TIS), eddy current inspect the shaft for a crack in the area of the weld, which must be done by a Level II or Level III inspector certified in the eddy current fault detection method in the Aeronautics Sector according to the EN4179 or NAS410 standard. (3) For Model EC225LP, either do paragraphs (3)(i) and (3)(ii) or do paragraph (3)(iii). (i) Before further flight, install a placard in full view of the pilot with the following statement in red, 6 millimeter letters on a white background: ‘‘MAXIMUM CONTINUOUS TORQUE LIMITED TO 70% DURING LEVEL FLIGHTS AT IAS EQUAL TO OR MORE THAN 60 KTS,’’ and (ii) Before further flight and thereafter at intervals not to exceed 11.5 hours TIS, remove the main jet and emergency spraying jet, and ultrasonic inspect the shaft in the weld area for a crack, which must be done by a Level II or Level III inspector certified in the eddy current fault detection method in the Aeronautics Sector according to the EN4179 or NAS410 standard, or (iii) Before further flight, and thereafter at intervals not to exceed 8 hours TIS, remove the main jet and emergency spraying jet, and ultrasonic inspect the shaft for a crack in the area of the weld, which must be done by a Level II or Level III operator certified in the ultrasonic fault detection method in the Aeronautics Sector according to the EN4179 or NAS410 standard. (4) If there is a crack, before further flight, replace the shaft with an airworthy part. wreier-aviles on DSK5TPTVN1PROD with RULES (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to Rao Edupuganti, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email rao.edupuganti@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (g) Additional Information (1) Eurocopter Alert Service Bulletin (ASB) No. AS332–01.00.82 and ASB No. EC225– 04A009, both Revision 3, both dated July 8, 2013, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http:// www.eurocopter.com/techpub. You may review a copy of the service information at the FAA, Office of the Regional Counsel, VerDate Mar<15>2010 14:43 Sep 30, 2013 Jkt 232001 Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2013–0138R1, dated July 15, 2013. You may view the EASA AD at http:// www.regulations.gov by searching for and locating it in the Docket for this AD. (h) Subject Joint Aircraft Service Component (JASC) Code: 6320 Main rotor gearbox. Issued in Fort Worth, Texas, on September 9, 2013. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2013–23580 Filed 9–30–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOMELAND SECURITY Customs and Border Protection DEPARTMENT OF THE TREASURY 19 CFR Parts 10, 24, 162, 163, and 178 [USCBP–2012–0017; CBP Dec. 13–16] RIN 1515–AD88 United States-Colombia Trade Promotion Agreement U.S. Customs and Border Protection, Department of Homeland Security; Department of the Treasury. ACTION: Final rule. AGENCY: This document adopts as a final rule, with some changes, interim amendments to the U.S. Customs and Border Protection (CBP) regulations which were published in the Federal Register on September 26, 2012, as CBP Dec. 12–16, to implement the preferential tariff treatment and other customs-related provisions of the United States-Colombia Trade Promotion Agreement. DATES: Effective October 31, 2013. FOR FURTHER INFORMATION CONTACT: Textile Operational Aspects: Jacqueline Sprungle, Trade Policy and Programs, Office of International Trade, (202) 863– 6517. Other Operational Aspects: Katrina Chang, Trade Policy and Programs, Office of International Trade, (202) 863– 6532. Legal Aspects: Karen Greene, Regulations and Rulings, Office of International Trade, (202) 325–0041. SUPPLEMENTARY INFORMATION: SUMMARY: Background On November 22, 2006, the United States and Colombia signed the United PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 60191 States-Colombia Trade Promotion Agreement (‘‘CTPA’’ or ‘‘Agreement’’), and on June 28, 2007, the Parties signed a protocol amending the Agreement. On October 21, 2011, the President signed into law the United States-Colombia Trade Promotion Agreement Implementation Act (the ‘‘Act’’), Public Law 112–42, 125 Stat. 462 (19 U.S.C. 3805 note), which approved and made statutory changes to implement the CTPA. On September 26, 2012, CBP published CBP Dec. 12–16 in the Federal Register (77 FR 59064) setting forth interim amendments to implement the preferential tariff treatment and other customs-related provisions of the CTPA and the Act. Please refer to those documents for further background information. The majority of the CTPA implementing regulations set forth in CBP Dec. 12–16 and adopted as final in this document have been included within Subpart T of Part 10 of the CBP regulations (19 CFR Part 10). However, in those cases in which CTPA implementation is more appropriate in the context of an existing regulatory provision, the CTPA regulatory text has been incorporated into an existing Part within the CBP regulations. CBP Dec. 12–16 also sets forth a number of crossreferences and other consequential changes to existing regulatory provisions to clarify the relationship between those existing provisions and the new CTPA implementing regulations. Although the interim regulatory amendments were promulgated without prior public notice and comment procedures and took effect on September 26, 2012, CBP Dec. 12–16 provided for the submission of public comments which would be considered before adoption of the interim regulations as a final rule. The prescribed public comment closed on November 26, 2012. CBP received no comments on CBP Dec. 12–16. Conclusion After further review of the matter, and in light of the fact that no comments were submitted in response to CBP’s solicitation of public comment, CBP has determined to adopt as final, with the changes described below, the interim rule published in the Federal Register (77 FR 59064) on September 26, 2012. The changes in this document are set forth below: • Amend § 10.3007(a) to clarify, as per Article 4.17.2 of the CTPA, that an importer that claims preferential tariff treatment for a good imported into the United States under § 10.3003(b), based E:\FR\FM\01OCR1.SGM 01OCR1

Agencies

[Federal Register Volume 78, Number 190 (Tuesday, October 1, 2013)]
[Rules and Regulations]
[Pages 60188-60191]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-23580]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0807; Directorate Identifier 2013-SW-035-AD; 
Amendment 39-17601; AD 2013-19-19]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France (Eurocopter) 
Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for 
Eurocopter Model AS332C, AS332L, AS332L1, AS332L2, and EC225LP 
helicopters. This AD requires replacing certain serial-numbered main 
gearbox (MGB) bevel gear vertical shafts because they are no longer 
airworthy. Also, this AD requires certain inspections of each MGB bevel 
gear vertical shaft (shaft) for a crack. Also, this AD requires if 
there is a crack, replacing the shaft with an airworthy part before 
further flight. This AD is prompted by two incidents of emergency 
ditching after warning indications of loss of MGB oil pressure. These 
actions are intended to detect a cracked shaft, which could result in 
loss of MGB oil pressure, loss of the MGB lubrication system, and 
subsequent loss of control of the helicopter.

DATES: This AD becomes effective October 16, 2013.

[[Page 60189]]

    We must receive comments on this AD by December 2, 2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the European Aviation Safety 
Agency (EASA) AD, the economic evaluation, any comments received, and 
other information. The street address for the Docket Operations Office 
(telephone 800-647-5527) is in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.
    For service information identified in this AD, contact American 
Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052; 
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at 
http://www.eurocopter.com/techpub.
    You may review the referenced service information at the FAA, 
Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., 
Room 663, Fort Worth, Texas 76137.

FOR FURTHER INFORMATION CONTACT: Rao Edupuganti, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; 
email rao.edupuganti@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments prior to it becoming effective. However, we 
invite you to participate in this rulemaking by submitting written 
comments, data, or views. We also invite comments relating to the 
economic, environmental, energy, or federalism impacts that resulted 
from adopting this AD. The most helpful comments reference a specific 
portion of the AD, explain the reason for any recommended change, and 
include supporting data. To ensure the docket does not contain 
duplicate comments, commenters should send only one copy of written 
comments, or if comments are filed electronically, commenters should 
submit them only one time. We will file in the docket all comments that 
we receive, as well as a report summarizing each substantive public 
contact with FAA personnel concerning this rulemaking during the 
comment period. We will consider all the comments we receive and may 
conduct additional rulemaking based on those comments.

Discussion

    We are adopting a new AD for the specified Eurocopter helicopters 
with certain part-numbered shafts. This AD requires replacing certain 
serial-numbered shafts because they are no longer airworthy. Also, this 
AD requires certain inspections at specified intervals of each shaft 
for a crack. This AD also requires if there is a crack, replacing the 
shaft with an airworthy part before further flight. This AD is prompted 
by two incidents of emergency ditching after warning indication of loss 
of oil pressure. A full circumferential crack of the lower shaft 
occurred in the area where two sections of the shaft are welded 
together. As a result, the shaft stopped driving the main and backup 
oil pumps leading to warning indications of the loss of the MGB 
lubrication. The crew activated the MGB emergency lubrication system, 
and following a warning that indicated failure of that system, 
performed a controlled ditching into the sea. These actions are 
intended to detect a cracked shaft, which could result in loss of MGB 
oil pressure, loss of the MGB lubrication system, and subsequent loss 
of control of the helicopter.
    This AD is prompted by EASA AD 2013-0138R1, dated July 15, 2013, 
issued by EASA, which is the Technical Agent for the Member States of 
the European Union. EASA AD 2013-0138R1 was issued to revise EASA AD 
2013-0138-E, dated July 9, 2013, which superseded EASA Emergency AD 
2012-1250-E, dated November 21, 2012, to correct an unsafe condition 
for the Eurocopter Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and 
EC225LP helicopters, all serial numbers, with certain part-numbered 
shafts, installed.
    EASA advises of two events of the Model EC225LP helicopters. In 
both cases, an emergency ditching was performed after warning 
indication of MGB loss of oil pressure and subsequent additional red 
alarm on the MGB emergency lubrication system (EMLUB). EASA also 
advises of a full circumferential crack of the lower vertical shaft of 
the MGB bevel gear in the area where the two sections of the shaft are 
welded together. As a result, the vertical shaft ceased to drive the 
main and backup oil pumps leading to warning indications of the loss of 
the MGB main and standby oil lubrication systems. The crew activated 
the EMLUB system and, following a subsequent warning indicating failure 
of that system, performed a controlled ditching into the sea.
    EASA advises that Eurocopter determined after investigating the 
incidents that the MGB bevel gear vertical shaft failures resulted from 
a combination of factors, including stress hot-spots induced by the 
shaft geometry, residual stresses in the shaft weld material resulting 
from the manufacturing process, and corrosion pitting inside the shaft 
on areas where gear spline wear particles accumulated.
    The EASA AD allows continued operations under certain conditions if 
equipped with a Vibration Health Monitoring System (VHM).

FAA's Determination

    These helicopters have been approved by the aviation authority of 
France and are approved for operation in the United States. Pursuant to 
our bilateral agreement with France, EASA, its technical 
representative, has notified us of the unsafe condition described in 
the EASA AD. We are issuing this AD because we evaluated all 
information provided by EASA and determined the unsafe condition exists 
and is likely to exist or develop on other helicopters of these same 
type designs.

Interim Action

    We consider this AD interim action. The design approval holder is 
currently developing a newly-designed shaft that will address the 
unsafe condition identified in this AD. Once the newly-designed shaft 
is developed, approved, and available, we might consider additional 
rulemaking.

Related Service Information

    Eurocopter has issued the following service information:
     ASB No. AS332-01.00.82, Revision 3, dated July 8, 2013, 
for the Model AS332C, C1, L, L1, L2 civil helicopters and Model AS332B, 
B1, M, M1, and F1 military model helicopters. The ASB defines the new 
inspection

[[Page 60190]]

requirements to detect a crack in the shaft.
     ASB No. EC225-04A009, Revision 3, dated July 8, 2013 for 
Model EC225LP helicopters. The ASB defines the new inspection 
requirements to detect a crack in the shaft.

AD Requirements

    This AD requires:
     Removing certain part-numbered and serial-numbered shafts 
from service, which are no longer considered airworthy.
     For certain model helicopters, before further flight and 
at specified intervals, eddy current inspecting the shaft for a crack 
in the area of the weld.
     For Model EC225LP, before further flight, either 
installing a placard in full view of the pilot with the following 
statement in red, 6 millimeter letters on a white background: ``MAXIMUM 
CONTINUOUS TORQUE LIMITED TO 70% DURING LEVEL FLIGHTS AT IAS EQUAL TO 
OR MORE THAN 60 KTS,'' and before further flight and thereafter at 
intervals not to exceed 11.5 hours TIS, removing the main jet and 
emergency spraying jet, and ultrasonic inspecting the shaft in the weld 
area for a crack; or
     Before further flight and thereafter at intervals not to 
exceed 8 hours TIS, removing the main jet and emergency spraying jet, 
and ultrasonic inspecting the shaft for a crack in the area of the 
weld.
     Each eddy current or ultrasonic inspection be done by a 
Level II or Level III operator certified in the ultrasonic fault 
detection method in the Aeronautics Sector according to the EN4179 or 
NAS410 standard.
     If there is a crack, before further flight, replacing the 
shaft with an airworthy part.

Differences Between This AD and the EASA AD

    The EASA AD allows continued operations under certain conditions if 
equipped with a VHM. The VHM system is validated by FAA for information 
only, and therefore we have not adopted that portion of the EASA AD.

Costs of Compliance

    We estimate that this AD will affect four helicopters of U.S. 
Registry.
    We estimate that operators may incur the following costs to comply 
with this AD. We estimate labor at $85 per work hour. Minimal cost to 
install a placard and 3 work hours to inspect each shaft for a crack, 
it will cost $255 per helicopter and $1,020 for the fleet per 
inspection. To replace a shaft, it will take 44 work hours and 
$1,243,350 for required parts for a total of $1,247,090 per helicopter.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments before adopting these 
AD requirements would delay implementing the safety actions needed to 
correct this known unsafe condition. Therefore, we find that the risk 
to the flying public justifies waiving notice and comment before 
adopting this rule because the required corrective actions must be done 
within 10 hours TIS and at repeated intervals within short periods of 
time.
    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined that notice and opportunity for 
public comment before issuing this AD are impracticable and that good 
cause exists for making this amendment effective in less than 30 days.

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.

Regulatory Findings

    We 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, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska to the extent that 
it justifies making a regulatory distinction; and
    4. 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 and placed it in the AD docket.

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:

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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2013-19-19 Eurocopter France: Amendment 39-17601; Docket No. FAA-
2013-0807; Directorate Identifier 2013-SW-035-AD.

(a) Applicability

    This AD applies to Eurocopter Model AS332C, AS332L, AS332L1, 
AS332L2, and EC225LP helicopters, with main gearbox (MGB) bevel gear 
vertical shaft (shaft), part number (P/N) 332A32-5101-00, 332A32-
5101-05, 332A32-5101-10, or 332A32-5101-15, certificated in any 
category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a cracked shaft 
resulting in loss of MGB oil pressure. These actions are intended to 
prevent loss of the MGB lubrication system and subsequent loss of 
control of the helicopter.

 (c) Effective Date

    This AD becomes effective October 16, 2013.

(d) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(e) Required Actions

    (1) Before further flight, remove shaft, P/N 332A32-5101-00, 
332A32-5101-05, 332A32-5101-10, or 332A32-5101-15, with S/N M330 
through M340 (inclusive) and S/N M370 through M5000 (inclusive) from 
service, which are no longer considered airworthy.

[[Page 60191]]

    (2) For Model AS332C, AS332L, AS332L1, and AS332L2 helicopters, 
before further flight and thereafter at intervals not to exceed 10 
hours time-in-service (TIS), eddy current inspect the shaft for a 
crack in the area of the weld, which must be done by a Level II or 
Level III inspector certified in the eddy current fault detection 
method in the Aeronautics Sector according to the EN4179 or NAS410 
standard.
    (3) For Model EC225LP, either do paragraphs (3)(i) and (3)(ii) 
or do paragraph (3)(iii).
    (i) Before further flight, install a placard in full view of the 
pilot with the following statement in red, 6 millimeter letters on a 
white background: ``MAXIMUM CONTINUOUS TORQUE LIMITED TO 70% DURING 
LEVEL FLIGHTS AT IAS EQUAL TO OR MORE THAN 60 KTS,'' and
    (ii) Before further flight and thereafter at intervals not to 
exceed 11.5 hours TIS, remove the main jet and emergency spraying 
jet, and ultrasonic inspect the shaft in the weld area for a crack, 
which must be done by a Level II or Level III inspector certified in 
the eddy current fault detection method in the Aeronautics Sector 
according to the EN4179 or NAS410 standard, or
    (iii) Before further flight, and thereafter at intervals not to 
exceed 8 hours TIS, remove the main jet and emergency spraying jet, 
and ultrasonic inspect the shaft for a crack in the area of the 
weld, which must be done by a Level II or Level III operator 
certified in the ultrasonic fault detection method in the 
Aeronautics Sector according to the EN4179 or NAS410 standard.
    (4) If there is a crack, before further flight, replace the 
shaft with an airworthy part.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to Rao Edupuganti, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-
5110; email rao.edupuganti@faa.gov.
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that you 
notify your principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office or 
certificate holding district office, before operating any aircraft 
complying with this AD through an AMOC.

(g) Additional Information

    (1) Eurocopter Alert Service Bulletin (ASB) No. AS332-01.00.82 
and ASB No. EC225-04A009, both Revision 3, both dated July 8, 2013, 
which are not incorporated by reference, contain additional 
information about the subject of this AD. For service information 
identified in this AD, contact American Eurocopter Corporation, 2701 
N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or 
(800) 232-0323; fax (972) 641-3775; or at http://www.eurocopter.com/techpub. You may review a copy of the service information at the 
FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham 
Blvd., Room 663, Fort Worth, Texas 76137.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) AD No. 2013-0138R1, dated July 15, 2013. You 
may view the EASA AD at http://www.regulations.gov by searching for 
and locating it in the Docket for this AD.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6320 Main rotor 
gearbox.

    Issued in Fort Worth, Texas, on September 9, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-23580 Filed 9-30-13; 8:45 am]
BILLING CODE 4910-13-P