Airworthiness Directives; Various Restricted Category Helicopters, 44434-44437 [2012-17607]

Download as PDF 44434 Federal Register / Vol. 77, No. 146 / Monday, July 30, 2012 / Rules and Regulations accordance with the Accomplishment Instructions of Gulfstream Service Bulletin 100–28–297, dated January 21, 2010. (3) If proper separation is found, and no sponge rubber padding is found, no further action is required by this paragraph. 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 AD: ■ 2012–15–06 Gulfstream Aerospace LP (Type Certificate Previously Held by Israel Aircraft Industries, Ltd.): Amendment 39–17135. Docket No. FAA–2010–1164; Directorate Identifier 2010–NM–057–AD. (a) Effective Date This airworthiness directive (AD) becomes effective September 4, 2012. (b) Affected ADs None. (c) Applicability This AD applies to Gulfstream Aerospace LP (Type Certificate previously held by Israel Aircraft Industries, Ltd.) Model Astra SPX, 1125 Westwind Astra, and Gulfstream 100 airplanes, serial numbers 002 through 158 inclusive, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 28: Fuel. (e) Reason This AD was prompted by a report indicating that sponge rubber padding was found between wheel well fuel lines and electrical harnesses. We are issuing this AD to detect and correct corrosion or chafing of the fuel lines, which could result in fuel leakage and possible fire in the wheel well area. tkelley on DSK3SPTVN1PROD with RULES (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Actions Within 24 months after the effective date of this AD, inspect for the presence of sponge rubber padding on the fuel lines in the wheel well area and inspect the fuel lines and electrical harnesses in the wheel well area for proper separation, in accordance with the Accomplishment Instructions of Gulfstream Service Bulletin 100–28–297, dated January 21, 2010. (1) If any sponge rubber padding is found, before further flight, remove all sponge rubber padding from the fuel lines, inspect the fuel lines that were covered with the rubber padding for any corrosion and repair or replace as applicable any corroded or chafed fuel lines, in accordance with the Accomplishment Instructions of Gulfstream Service Bulletin 100–28–297, dated January 21, 2010. (2) If any fuel lines and electrical harnesses are found to not have proper separation, before further flight, install loop clamps in VerDate Mar<15>2010 15:44 Jul 27, 2012 Jkt 226001 (h) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Tom Groves, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–1503; fax (425) 227–1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (i) Related Information Refer to MCAI Israeli Airworthiness Directive 28–10–02–01, dated February 22, 2010; and Gulfstream Service Bulletin 100– 28–297, dated January 21, 2010; for related information. (j) Material Incorporated by Reference (1) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part: (i) Gulfstream Service Bulletin 100–28– 297, dated January 21, 2010. (ii) Reserved. (2) For service information identified in this AD, contact Gulfstream Aerospace Corporation, P.O. Box 2206, Mail Station D–25, Savannah, Georgia 31402–2206; telephone 800–810–4853; fax 912–965–3520; email pubs@gulfstream.com; Internet https:// www.gulfstream.com/product_support/ technical_pubs/pubs/index.htm. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, 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 July 17, 2012. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–18153 Filed 7–27–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0488; Directorate Identifier 2008–SW–20–AD; Amendment 39– 17126; AD 2012–14–12] RIN 2120–AA64 Airworthiness Directives; Various Restricted Category Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for Arrow Falcon Exporters, Inc. (previously Utah State University); Firefly Aviation Helicopter Services (previously Erickson Air-Crane Co.); California Department of Forestry; Garlick Helicopters, Inc.; Global Helicopter Technology, Inc.; Hagglund Helicopters, LLC (previously Western International Aviation, Inc.); International Helicopters, Inc.; Precision Helicopters, LLC; Robinson Air Crane, Inc.; San Joaquin Helicopters (previously Hawkins and Powers Aviation, Inc.); S.M.&T. Aircraft (previously US Helicopters, Inc., UNC Helicopter, Inc., Southern Aero Corporation, and Wilco Aviation); Smith Helicopters; Southern Helicopter, Inc.; Southwest Florida Aviation International, Inc. (previously Jamie R. Hill and Southwest Florida Aviation); Tamarack Helicopters, Inc. (previously Ranger Helicopter Services, Inc.); US Helicopter, Inc. (previously UNC Helicopter, Inc.); West Coast Fabrication; and Williams Helicopter Corporation (previously Scott Paper Co.) Model HH–1K, TH–1F, TH–1L, UH–1A, UH–1B, UH–1E, UH–1F, UH–1H, UH– 1L, and UH–1P Helicopters; and Southwest Florida Aviation Model UH– 1B (SW204 and SW204HP) and UH–1H (SW205) Helicopters. This AD requires SUMMARY: E:\FR\FM\30JYR1.SGM 30JYR1 Federal Register / Vol. 77, No. 146 / Monday, July 30, 2012 / Rules and Regulations tkelley on DSK3SPTVN1PROD with RULES inspecting each affected tail rotor blade (blade) forward tip weight retention block (tip block) and the aft tip closure (tip closure) for adhesive bond voids and removing any blade with an excessive void from service. This AD also requires modifying certain blades by installing shear pins and tip closure rivets. This AD was prompted by reports of missing tip blocks or tip closures, resulting in minor to substantial damage to blades installed on Bell Model 212 and 412 helicopters. The actions are intended to prevent loss of a tip block or tip closure, loss of a blade, and subsequent loss of control of the helicopter. DATES: This AD is effective September 4, 2012. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of September 4, 2012. ADDRESSES: For service information identified in this AD, contact Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone (817) 280–3391; fax (817) 280–6466; or at https://www.bellcustomer.com/files/. You may review a copy of the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. Examining the AD Docket: You may examine the AD docket on the Internet at https://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, any incorporated-by-reference service information, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800– 647–5527) is U.S. Department of Transportation, Docket Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5170; email 7-avs-asw-170@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On May 13, 2010, at 75 FR 26889, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 to include an AD that would apply to Arrow Falcon Exporters, Inc. VerDate Mar<15>2010 15:44 Jul 27, 2012 Jkt 226001 (previously Utah State University); Firefly Aviation Helicopter Services (previously Erickson Air-Crane Co.); California Department of Forestry; Garlick Helicopters, Inc.; Global Helicopter Technology, Inc.; Hagglund Helicopters, LLC (previously Western International Aviation, Inc.); International Helicopters, Inc.; Precision Helicopters, LLC; Robinson Air Crane, Inc.; San Joaquin Helicopters (previously Hawkins and Powers Aviation, Inc.); S.M.&T. Aircraft (previously US Helicopters, Inc., UNC Helicopter, Inc., Southern Aero Corporation, and Wilco Aviation); Smith Helicopters; Southern Helicopter, Inc.; Southwest Florida Aviation International, Inc. (previously Jamie R. Hill and Southwest Florida Aviation); Tamarack Helicopters, Inc. (previously Ranger Helicopter Services, Inc.); US Helicopter, Inc. (previously UNC Helicopter, Inc.); West Coast Fabrication; and Williams Helicopter Corporation (previously Scott Paper Co.) Model HH–1K, TH–1F, TH–1L, UH–1A, UH–1B, UH–1E, UH–1F, UH–1H, UH– 1L, and UH–1P Helicopters; and Southwest Florida Aviation Model UH– 1B (SW204 and SW204HP) and UH–1H (SW205) Helicopters. This NPRM proposed to require inspecting each applicable blade tip block and tip closure for voids and removing any blade with an excessive void from service. The NPRM also proposed to require modifying certain blades by installing shear pins and tip closure rivets. The proposed requirements were intended to prevent loss of a tip block or tip closure, loss of a blade, and subsequent loss of control of the helicopter. AD 2002–09–04, Amendment 39– 12737 (67 FR 22349, May 3, 2002), was issued for the Bell Model 205A, 205A– 1, 205B, 212, 412, 412CF, and 412EP helicopters and contained the same requirements as those in this AD. AD 2007–22–02, Amendment 39–15238 (72 FR 60760, October 26, 2007), superseded AD 2002–09–04 to expand the applicability to include other partand serial-numbered blades. Some of the blades in the applicability of AD 2007–22–02 are eligible for installation on helicopters included in this AD, which may have an FAA-approved modification that increases the helicopter’s power rating to the equivalent of the Bell Model 205B or the 212 helicopter. The Bell Model 205B and 212 helicopters are addressed in AD 2007–22–02. Consequently, the inspections and modifications required by AD 2007–22–02 are mandated for the PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 44435 blades installed on helicopters included in this AD. Comments We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM. FAA’s Determination We have reviewed the relevant information and determined that an unsafe condition exists and is likely to exist or develop on other products of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed except we have revised the estimated costs of complying with this AD to reflect ten hours for inspection instead of three hours, and minor editorial changes. These minor editorial changes are consistent with the intent of the proposals in the NPRM and will not increase the scope of the AD. Related Service Information We have reviewed Bell Helicopter Textron Alert Service Bulletin No. 212– 00–111, Revision D, dated March 18, 2005 (ASB), which describes procedures for inspecting and modifying certain tail rotor blades. The ASB was issued as a result of an investigation of an in-flight loss of a blade tip block, part number (P/ N) 212–010–750–105. The investigation revealed the countersunk screws retaining the tip block were installed incorrectly, resulting in inadequate tip block retention. Reports have also been submitted about loss of the tip closures from other blades possibly because of inadequate adhesive bonding in this area. Costs of Compliance We estimate that this AD will affect 716 helicopters of U.S. registry, and 25 of those helicopters will have the increased power rating. Labor costs will average an estimated $85 per work hour. Based on these assumptions, we expect the following costs: • About 1 work hour to review the helicopter records for a labor cost of $85 per helicopter, $60,860 for the U.S. fleet. • About 10 work hours to inspect the affected blades, install the shear pins and tip closure rivets, reidentify, and dynamically balance the blade. Required supplies will cost about $45, for a total cost of $895 per helicopter. We assume that the blade sets are installed on 25 helicopters with the FAA-approved modification that will need to be inspected and repaired. E:\FR\FM\30JYR1.SGM 30JYR1 44436 Federal Register / Vol. 77, No. 146 / Monday, July 30, 2012 / Rules and Regulations 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 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 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. tkelley on DSK3SPTVN1PROD with RULES 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: ■ VerDate Mar<15>2010 15:44 Jul 27, 2012 Jkt 226001 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): ■ 2012–14–12 Arrow Falcon Exporters, Inc. (previously Utah State University); Firefly Aviation Helicopter Services (previously Erickson Air-Crane Co.); California Department of Forestry; Garlick Helicopters, Inc.; Global Helicopter Technology, Inc.; Hagglund Helicopters, LLC (previously Western International Aviation, Inc.); International Helicopters, Inc.; Precision Helicopters, LLC; Robinson Air Crane, Inc.; San Joaquin Helicopters (previously Hawkins and Powers Aviation, Inc.); S.M.&T. Aircraft (previously US Helicopters, Inc., UNC Helicopter, Inc., Southern Aero Corporation, and Wilco Aviation); Smith Helicopters; Southern Helicopter, Inc.; Southwest Florida Aviation International, Inc. (previously Jamie R. Hill and Southwest Florida Aviation); Tamarack Helicopters, Inc. (previously Ranger Helicopter Services, Inc.); US Helicopter, Inc. (previously UNC Helicopter, Inc.); West Coast Fabrication; and Williams Helicopter Corporation (previously Scott Paper Co.) Model HH–1K, TH–1F, TH–1L, UH–1A, UH–1B, UH–1E, UH–1F, UH–1H, UH–1L, and UH–1P Helicopters; and Southwest Florida Aviation Model UH–1B (SW204 and SW204HP) and UH–1H (SW205) Helicopters: Amendment 39–17126; Docket No. FAA–2010–0488; Directorate Identifier 2008–SW–20–AD. (a) Applicability (1) This AD applies to Model HH–1K, TH– 1F, TH–1L, UH–1A, UH–1B, UH–1E, UH–1F, UH–1H, UH–1L, and UH–1P helicopters, and Southwest Florida Aviation Model UH–1B series (SW204 series and SW204HP) and UH–1H series (SW205 series) helicopters, with a tail rotor blade (blade), part number (P/N) 212–010–750–009 through –129, all serial numbers except serial numbers with a prefix of ‘‘A’’ or ‘‘AFS,’’ and the number 11926, 13351, 13367, 13393, 13400, 13402, 13515, 13540, 13568, 13595 through 13602, 13619, and subsequent larger numbers, installed, certificated in any category. (2) A blade inspected and modified by following either AD 2002–09–04 (67 FR 22349, May 3, 2002) or AD 2007–22–02 (72 FR 60760, October 26, 2007), for the Bell Helicopter Textron (Bell) Model 205A, 205A– 1, 205B, 212, 412, 412CF, and 412EP helicopters satisfies the requirements of this AD. (b) Unsafe Condition This AD defines the unsafe condition as adhesive bond voids. This condition could result in loss of the forward tip weight retention block (tip block) or aft tip closure (tip closure), loss of the blade, and subsequent loss of control of the helicopter. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 (c) Effective Date This AD becomes effective September 4, 2012. (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 Within 100 hours time-in-service: (1) Inspect the tip block and tip closure of each blade for voids. Remove from service any blade with a void in excess of that allowed by the applicable maintenance or Component Repair and Overhaul Manual limitations. (2) Inspect the tip block attachment countersink screws in the four locations to determine if the head of each countersunk screw is flush with the surface of the abrasion strip. The locations of these four screws are depicted on Figure 1 of Bell Alert Service Bulletin 212–00–111, Revision D, dated March 18, 2005 (ASB). If any of these screws are set below the surface of the abrasion strip or are covered with filler material, install shear pins by following the Accomplishment Instructions, Part A, Shear Pin Installation paragraphs, of the ASB. (3) Install the tip closure rivets on each blade, re-identify the modified blade by adding an ‘‘FM’’ after the P/N, and dynamically balance the tail rotor hub assembly by following the Accomplishment Instructions, Part B, Aft Tip Closure Rivet Installation paragraphs, of the ASB. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, may approve AMOCs for this AD. Send your proposal to: Michael Kohner, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5170; email 7-avs-asw170@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) Subject Joint Aircraft Service Component (JASC) Code: 6410, Tail Rotor Blades. (h) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Bell Helicopter Textron Alert Service Bulletin No. 212–00–111, Revision D, dated March 18, 2005. E:\FR\FM\30JYR1.SGM 30JYR1 Federal Register / Vol. 77, No. 146 / Monday, July 30, 2012 / Rules and Regulations (ii) Reserved. (3) For service information identified in this AD, contact Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone (817) 280–3391; fax (817) 280– 6466; or at https://www.bellcustomer.com/ files/. (4) 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. (5) You may also review a copy of the service information that is incorporated by reference 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. This AD becomes effective September 4, 2012. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 4, 2012. Comments You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. EMBRAER requested that we revise the NPRM (76 FR 72855, November 28, 2011) to include EMBRAER Service Bulletin 190LIN–32–0014, dated February 10, 2011 (for Model 190–100 ECJ airplanes); and EMBRAER Service Bulletin 190LIN–32–0015, dated February 10, 2011 (for Model 190–100 ECJ airplanes); as additional service information for the inspection and replacement of the MLG retraction actuator, bolt, and anti-rotation pin. We agree with EMBRAER’s request to add additional service information to this AD. EMBRAER Service Bulletin 190LIN–32–0014, dated February 10, 2011 (for Model 190–100 ECJ airplanes), provides procedures for doing the inspection; and EMBRAER Service Bulletin 190LIN–32–0015, dated February 10, 2011 (for Model 190–100 ECJ airplanes, provides procedures for the replacement. The procedures to do the inspection and replacement are essentially the same as those specified in EMBRAER Service Bulletin 190–32– 0036, dated October 4, 2010 (for Model ERJ 190 airplanes); and EMBRAER Service Bulletin 190–32–0037, dated October 6, 2010 (for Model ERJ 190 airplanes). We have revised this AD accordingly. DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: Cindy Ashforth, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–2768; fax (425) 227–1149. Issued in Fort Worth, Texas, on July 10, 2012. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. SUPPLEMENTARY INFORMATION: [FR Doc. 2012–17607 Filed 7–27–12; 8:45 am] Discussion BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–1251; Directorate Identifier 2011–NM–017–AD; Amendment 39–17132; AD 2012–15–03] RIN 2120–AA64 Airworthiness Directives; Embraer S.A. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 190 airplanes. This AD was prompted by a report of damage on the rod end of the retracting actuator rod of the main landing gear (MLG). This AD requires performing a one-time general visual inspection to determine if a certain part number is installed on the MLG retraction actuator; if necessary, performing a general visual inspection for discrepancies between the actuator rod end and shock strut lug of the MLG retraction actuator; and corrective actions if necessary. We are issuing this AD to detect and correct breakage of the MLG retracting actuator rod, which may result in MLG extension with no hydraulic damping and consequent damage to the locking mechanism and collapse of the MLG. tkelley on DSK3SPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 15:44 Jul 27, 2012 Jkt 226001 44437 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on November 28, 2011 (76 FR 72855). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: It has been found the occurrence of damage on the rod end of the Main Landing Gear (MLG) retraction actuator. The ANAC ˆ [Agencia Nacional de Aviacao Civil] is ¸˜ issuing this AD to prevent breakage of the MLG retracting actuator rod, which may result in MLG extension with no hydraulic damping and consequent damage to the locking mechanism and collapse of the MLG. * * * * * Required actions include a one-time general visual inspection to determine if a certain part number is installed on the left-hand and right-hand MLG retraction actuator, and if necessary, a general visual inspection for discrepancies (such as cracks, damage, and movement) between the actuator rod end and shock strut lug of the MLG retraction actuator. The corrective actions include: If any discrepancy is found during any inspection, including any movement between the actuator rod-end and shock strut lug, replace the MLG retraction actuator, and as applicable, replace the anti-rotation pin and the attachment bolt with a new pin and bolt; replace the actuator with a new actuator having a certain part number, and modify the attachment points. You may obtain further information by examining the MCAI in the AD docket. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 We gave the public the opportunity to participate in developing this AD. We considered the comments received. Request To Use Additional Service Bulletins Request To Allow Flight After Damage Is Found EMBRAER requested that we revise the NPRM (76 FR 72855, November 28, 2011) to allow further flight within 500 flight cycles after any damage is found on the airplane. EMBRAER stated that EMBRAER Service Bulletin 190LIN–32– 0014, dated February 10, 2011 (for Model 190–100 ECJ airplanes); EMBRAER Service Bulletin 190LIN–32– 0015, dated February 10, 2011 (for Model 190–100 ECJ airplanes); and Brazilian Airworthiness Directive 2011– 02–01, dated February 12, 2011; allows replacement of the MLG retraction actuator, the attachment bolt, and the anti-rotation pin within the next 500 flight cycles if any discrepancy is found. EMBRAER stated that the NPRM requires that any discrepancy found be replaced before further flight. We disagree with EMBRAER’s request to allow further flight within 500 flight cycles after any damage is found on the airplane. Our policy requires repair of known cracks or damage before further flight (though we might make E:\FR\FM\30JYR1.SGM 30JYR1

Agencies

[Federal Register Volume 77, Number 146 (Monday, July 30, 2012)]
[Rules and Regulations]
[Pages 44434-44437]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-17607]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0488; Directorate Identifier 2008-SW-20-AD; 
Amendment 39-17126; AD 2012-14-12]
RIN 2120-AA64


Airworthiness Directives; Various Restricted Category Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for Arrow 
Falcon Exporters, Inc. (previously Utah State University); Firefly 
Aviation Helicopter Services (previously Erickson Air-Crane Co.); 
California Department of Forestry; Garlick Helicopters, Inc.; Global 
Helicopter Technology, Inc.; Hagglund Helicopters, LLC (previously 
Western International Aviation, Inc.); International Helicopters, Inc.; 
Precision Helicopters, LLC; Robinson Air Crane, Inc.; San Joaquin 
Helicopters (previously Hawkins and Powers Aviation, Inc.); S.M.&T. 
Aircraft (previously US Helicopters, Inc., UNC Helicopter, Inc., 
Southern Aero Corporation, and Wilco Aviation); Smith Helicopters; 
Southern Helicopter, Inc.; Southwest Florida Aviation International, 
Inc. (previously Jamie R. Hill and Southwest Florida Aviation); 
Tamarack Helicopters, Inc. (previously Ranger Helicopter Services, 
Inc.); US Helicopter, Inc. (previously UNC Helicopter, Inc.); West 
Coast Fabrication; and Williams Helicopter Corporation (previously 
Scott Paper Co.) Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, 
UH-1H, UH-1L, and UH-1P Helicopters; and Southwest Florida Aviation 
Model UH-1B (SW204 and SW204HP) and UH-1H (SW205) Helicopters. This AD 
requires

[[Page 44435]]

inspecting each affected tail rotor blade (blade) forward tip weight 
retention block (tip block) and the aft tip closure (tip closure) for 
adhesive bond voids and removing any blade with an excessive void from 
service. This AD also requires modifying certain blades by installing 
shear pins and tip closure rivets. This AD was prompted by reports of 
missing tip blocks or tip closures, resulting in minor to substantial 
damage to blades installed on Bell Model 212 and 412 helicopters. The 
actions are intended to prevent loss of a tip block or tip closure, 
loss of a blade, and subsequent loss of control of the helicopter.

DATES: This AD is effective September 4, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of September 4, 
2012.

ADDRESSES: For service information identified in this AD, contact Bell 
Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone 
(817) 280-3391; fax (817) 280-6466; or at https://www.bellcustomer.com/files/. You may review a copy of the referenced service information at 
the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham 
Blvd., Room 663, Fort Worth, Texas 76137.
    Examining the AD Docket: You may examine the AD docket on the 
Internet at https://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, any 
incorporated-by-reference service information, the economic evaluation, 
any comments received, and other information. The street address for 
the Docket Operations Office (phone: 800-647-5527) is U.S. Department 
of Transportation, Docket Operations Office, M-30, West Building Ground 
Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety 
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5170; 
email 7-avs-asw-170@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    On May 13, 2010, at 75 FR 26889, the Federal Register published our 
notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR 
part 39 to include an AD that would apply to Arrow Falcon Exporters, 
Inc. (previously Utah State University); Firefly Aviation Helicopter 
Services (previously Erickson Air-Crane Co.); California Department of 
Forestry; Garlick Helicopters, Inc.; Global Helicopter Technology, 
Inc.; Hagglund Helicopters, LLC (previously Western International 
Aviation, Inc.); International Helicopters, Inc.; Precision 
Helicopters, LLC; Robinson Air Crane, Inc.; San Joaquin Helicopters 
(previously Hawkins and Powers Aviation, Inc.); S.M.&T. Aircraft 
(previously US Helicopters, Inc., UNC Helicopter, Inc., Southern Aero 
Corporation, and Wilco Aviation); Smith Helicopters; Southern 
Helicopter, Inc.; Southwest Florida Aviation International, Inc. 
(previously Jamie R. Hill and Southwest Florida Aviation); Tamarack 
Helicopters, Inc. (previously Ranger Helicopter Services, Inc.); US 
Helicopter, Inc. (previously UNC Helicopter, Inc.); West Coast 
Fabrication; and Williams Helicopter Corporation (previously Scott 
Paper Co.) Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-
1H, UH-1L, and UH-1P Helicopters; and Southwest Florida Aviation Model 
UH-1B (SW204 and SW204HP) and UH-1H (SW205) Helicopters. This NPRM 
proposed to require inspecting each applicable blade tip block and tip 
closure for voids and removing any blade with an excessive void from 
service. The NPRM also proposed to require modifying certain blades by 
installing shear pins and tip closure rivets. The proposed requirements 
were intended to prevent loss of a tip block or tip closure, loss of a 
blade, and subsequent loss of control of the helicopter.
    AD 2002-09-04, Amendment 39-12737 (67 FR 22349, May 3, 2002), was 
issued for the Bell Model 205A, 205A-1, 205B, 212, 412, 412CF, and 
412EP helicopters and contained the same requirements as those in this 
AD. AD 2007-22-02, Amendment 39-15238 (72 FR 60760, October 26, 2007), 
superseded AD 2002-09-04 to expand the applicability to include other 
part- and serial-numbered blades. Some of the blades in the 
applicability of AD 2007-22-02 are eligible for installation on 
helicopters included in this AD, which may have an FAA-approved 
modification that increases the helicopter's power rating to the 
equivalent of the Bell Model 205B or the 212 helicopter. The Bell Model 
205B and 212 helicopters are addressed in AD 2007-22-02. Consequently, 
the inspections and modifications required by AD 2007-22-02 are 
mandated for the blades installed on helicopters included in this AD.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM.

FAA's Determination

    We have reviewed the relevant information and determined that an 
unsafe condition exists and is likely to exist or develop on other 
products of these same type designs and that air safety and the public 
interest require adopting the AD requirements as proposed except we 
have revised the estimated costs of complying with this AD to reflect 
ten hours for inspection instead of three hours, and minor editorial 
changes. These minor editorial changes are consistent with the intent 
of the proposals in the NPRM and will not increase the scope of the AD.

Related Service Information

    We have reviewed Bell Helicopter Textron Alert Service Bulletin No. 
212-00-111, Revision D, dated March 18, 2005 (ASB), which describes 
procedures for inspecting and modifying certain tail rotor blades. The 
ASB was issued as a result of an investigation of an in-flight loss of 
a blade tip block, part number (P/N) 212-010-750-105. The investigation 
revealed the countersunk screws retaining the tip block were installed 
incorrectly, resulting in inadequate tip block retention. Reports have 
also been submitted about loss of the tip closures from other blades 
possibly because of inadequate adhesive bonding in this area.

Costs of Compliance

    We estimate that this AD will affect 716 helicopters of U.S. 
registry, and 25 of those helicopters will have the increased power 
rating. Labor costs will average an estimated $85 per work hour. Based 
on these assumptions, we expect the following costs:
     About 1 work hour to review the helicopter records for a 
labor cost of $85 per helicopter, $60,860 for the U.S. fleet.
     About 10 work hours to inspect the affected blades, 
install the shear pins and tip closure rivets, reidentify, and 
dynamically balance the blade. Required supplies will cost about $45, 
for a total cost of $895 per helicopter. We assume that the blade sets 
are installed on 25 helicopters with the FAA-approved modification that 
will need to be inspected and repaired.

[[Page 44436]]

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

    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 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):

2012-14-12 Arrow Falcon Exporters, Inc. (previously Utah State 
University); Firefly Aviation Helicopter Services (previously 
Erickson Air-Crane Co.); California Department of Forestry; Garlick 
Helicopters, Inc.; Global Helicopter Technology, Inc.; Hagglund 
Helicopters, LLC (previously Western International Aviation, Inc.); 
International Helicopters, Inc.; Precision Helicopters, LLC; 
Robinson Air Crane, Inc.; San Joaquin Helicopters (previously 
Hawkins and Powers Aviation, Inc.); S.M.&T. Aircraft (previously US 
Helicopters, Inc., UNC Helicopter, Inc., Southern Aero Corporation, 
and Wilco Aviation); Smith Helicopters; Southern Helicopter, Inc.; 
Southwest Florida Aviation International, Inc. (previously Jamie R. 
Hill and Southwest Florida Aviation); Tamarack Helicopters, Inc. 
(previously Ranger Helicopter Services, Inc.); US Helicopter, Inc. 
(previously UNC Helicopter, Inc.); West Coast Fabrication; and 
Williams Helicopter Corporation (previously Scott Paper Co.) Model 
HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and 
UH-1P Helicopters; and Southwest Florida Aviation Model UH-1B (SW204 
and SW204HP) and UH-1H (SW205) Helicopters: Amendment 39-17126; 
Docket No. FAA-2010-0488; Directorate Identifier 2008-SW-20-AD.

(a) Applicability

    (1) This AD applies to Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, 
UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P helicopters, and Southwest 
Florida Aviation Model UH-1B series (SW204 series and SW204HP) and 
UH-1H series (SW205 series) helicopters, with a tail rotor blade 
(blade), part number (P/N) 212-010-750-009 through -129, all serial 
numbers except serial numbers with a prefix of ``A'' or ``AFS,'' and 
the number 11926, 13351, 13367, 13393, 13400, 13402, 13515, 13540, 
13568, 13595 through 13602, 13619, and subsequent larger numbers, 
installed, certificated in any category.
    (2) A blade inspected and modified by following either AD 2002-
09-04 (67 FR 22349, May 3, 2002) or AD 2007-22-02 (72 FR 60760, 
October 26, 2007), for the Bell Helicopter Textron (Bell) Model 
205A, 205A-1, 205B, 212, 412, 412CF, and 412EP helicopters satisfies 
the requirements of this AD.

(b) Unsafe Condition

    This AD defines the unsafe condition as adhesive bond voids. 
This condition could result in loss of the forward tip weight 
retention block (tip block) or aft tip closure (tip closure), loss 
of the blade, and subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective September 4, 2012.

(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

    Within 100 hours time-in-service:
    (1) Inspect the tip block and tip closure of each blade for 
voids. Remove from service any blade with a void in excess of that 
allowed by the applicable maintenance or Component Repair and 
Overhaul Manual limitations.
    (2) Inspect the tip block attachment countersink screws in the 
four locations to determine if the head of each countersunk screw is 
flush with the surface of the abrasion strip. The locations of these 
four screws are depicted on Figure 1 of Bell Alert Service Bulletin 
212-00-111, Revision D, dated March 18, 2005 (ASB). If any of these 
screws are set below the surface of the abrasion strip or are 
covered with filler material, install shear pins by following the 
Accomplishment Instructions, Part A, Shear Pin Installation 
paragraphs, of the ASB.
    (3) Install the tip closure rivets on each blade, re-identify 
the modified blade by adding an ``FM'' after the P/N, and 
dynamically balance the tail rotor hub assembly by following the 
Accomplishment Instructions, Part B, Aft Tip Closure Rivet 
Installation paragraphs, of the ASB.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Rotorcraft Certification Office, Rotorcraft 
Directorate, FAA, may approve AMOCs for this AD. Send your proposal 
to: Michael Kohner, Aviation Safety Engineer, Rotorcraft 
Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham 
Blvd., Fort Worth, Texas 76137; telephone (817) 222-5170; email 7-avs-asw-170@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) Subject

    Joint Aircraft Service Component (JASC) Code: 6410, Tail Rotor 
Blades.

(h) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information listed in this 
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Bell Helicopter Textron Alert Service Bulletin No. 212-00-
111, Revision D, dated March 18, 2005.

[[Page 44437]]

    (ii) Reserved.
    (3) For service information identified in this AD, contact Bell 
Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; 
telephone (817) 280-3391; fax (817) 280-6466; or at https://www.bellcustomer.com/files/.
    (4) 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.
    (5) You may also review a copy of the service information that 
is incorporated by reference 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.

    Issued in Fort Worth, Texas, on July 10, 2012.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-17607 Filed 7-27-12; 8:45 am]
BILLING CODE 4910-13-P

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