Airworthiness Directives; Enstrom Helicopter Corporation Helicopters, 36131-36134 [2012-14634]

Download as PDF Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations (1) Bombardier, Inc. Model CL–600–2C10 (Regional Jet Series 700, 701, & 702) airplanes, serial numbers 10003 through 10331 inclusive. (2) Bombardier, Inc. Model CL–600–2D15 (Regional Jet Series 705) and CL–600–2D24 (Regional Jet Series 900) airplanes, serial numbers 15001 through 15279 inclusive. (d) Subject Air Transport Association (ATA) of America Code 36: Pneumatic. (e) Reason This AD was prompted by reports of a bleed air leak from the high pressure ducts which was not immediately detected by the bleed leak detection system. We are issuing this AD to prevent an undetected bleed air leak which can cause loss of rudder control, can lead to degradation of structural integrity, and could be a potential heat source that can lead to fuel being ignited. (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) Install Protective Shields For Model CL–600–2C10 airplanes having serial numbers 10003 through 10326 inclusive, and Model CL–600–2D15 and CL– 600–2D24 airplanes having serial numbers 15001 through 15267 inclusive: Within 6,600 flight hours or 24 months after the effective date of this AD, whichever occurs first, install protective shields on the rudder quadrant support-beam in the aft equipment compartment, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 670BA–36–014, Revision A, dated October 11, 2011. srobinson on DSK4SPTVN1PROD with RULES (h) Install Protective Blankets and Sensing Elements For Model CL–600–2C10 airplanes having serial numbers 10003 through 10331 inclusive and Models CL–600–2D15 and CL– 600–2D24 airplanes having serial numbers 15001 through 15279 inclusive: Within 6,600 flight hours or 24 months after the effective date of this AD, whichever occurs first, install protective blankets on the upper surface of the wing box and fuel components, and install new sensing elements in the wheel well of the main landing gear and the overwing area, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 670BA–36–016, Revision A, dated October 11, 2011. (i) Credit for Previous Actions This paragraph provides credit for installations, required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 670BA– 36–014 or 670BA–36–016, both dated April 7, 2011, as applicable. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft VerDate Mar<15>2010 16:18 Jun 15, 2012 Jkt 226001 Certification Office, ANE–170, 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 ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone 516–228–7300; fax 516–794–5531. 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. (k) Related Information Refer to MCAI Canadian Airworthiness Directive CF–2012–06, dated January 26, 2012, and the service bulletins specified in paragraphs (k)(1) and (k)(2) of this AD, for related information. (1) Bombardier Service Bulletin 670BA– 36–014, Revision A, dated October 11, 2011. (2) Bombardier Service Bulletin 670BA– 36–016, Revision A, dated October 11, 2011. (l) Material Incorporated by Reference (1) 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 51. (2) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. (i) Bombardier Service Bulletin 670BA–36– 014, Revision A, dated October 11, 2011. (ii) Bombardier Service Bulletin 670BA– 36–016, Revision A, dated October 11, 2011. (3) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote´ Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; email thd.crj@aero.bombardier.com; Internet https:// www.bombardier.com. (4) 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. (5) 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. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 36131 Issued in Renton, Washington, on May 31, 2012. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–14042 Filed 6–15–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0562; Directorate Identifier 2012–SW–038–AD; Amendment 39–17068; AD 2012–11–05] RIN 2120–AA64 Airworthiness Directives; Enstrom Helicopter Corporation Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are superseding an existing airworthiness directive (AD) for Enstrom Helicopter Corporation (Enstrom) Model F–28C, F–28C–2, F– 28F, 280C, 280F, 280FX, TH–28, 480, and 480B helicopters to add another trim relay to the applicability and to revise the modification instructions. This AD is prompted by the discovery that another part-numbered trim relay, inadvertently omitted from the current AD, may contain the same unsafe condition. These actions are intended to prevent failure of the cyclic trim system and subsequent loss of control of the helicopter. SUMMARY: This AD becomes effective July 3, 2012. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 3, 2012. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of January 23, 2012 (77 FR 729, January 6, 2012). We must receive comments on this AD by August 17, 2012. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to https://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 DATES: E:\FR\FM\18JNR1.SGM 18JNR1 36132 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations srobinson on DSK4SPTVN1PROD with RULES 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 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, 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 Enstrom Helicopter Corporation, 2209 22nd St., Menominee, Michigan, 49858–0490; telephone: 906– 863–1200; email: customerservice@ enstromhelicopter.com; Web site: https://www.enstromhelicopter.com/ enstrom_new/enstrom_support_tec. html. 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. FOR FURTHER INFORMATION CONTACT: Gregory J. Michalik, Enstrom Program Manager, FAA, Chicago Aircraft Certification Office, 2300 East Devon Avenue, Room 107, Des Plaines, Illinois, 60018; telephone (847) 294–7135; email: gregory.michalik@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 VerDate Mar<15>2010 16:18 Jun 15, 2012 Jkt 226001 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 On December 14, 2011, we issued AD 2011–26–10, amendment 39–16900 (77 FR 729, January 6, 2012) for Enstrom Model F–28C, F–28C–2, F–28F, 280C, 280F, 280FX, TH–28, 480, and 480B helicopters with a trim relay, partnumber (P/N) KUP14D55–472, M83536/ 10–015M, or M83536/10–024M. That AD requires modifying the lateral and longitudinal trim actuator assemblies by replacing the actuator and limit switch bracket to provide a positive stop for the trim actuator. In the event of a trim actuator runaway, the new bracket will stop the actuator, causing the circuit breaker to trip before any significant loss of control occurs. After the trim actuator assemblies are modified, that AD requires performing operational (ground) and flight tests to determine that the trim relay is working correctly. That AD was prompted by reports of 4 failures in the cyclic trim system in the field, 2 that occurred on the Enstrom Model 480B helicopter and 2 that occurred on the Enstrom Model F28 helicopter. These failures resulted in reduced controllability of the helicopter. We issued that AD to prevent failure of the cyclic trim system and subsequent loss of control of the helicopter. Comments Since we issued immediately adopted AD 2011–26–10, we received one comment from Enstrom, the manufacturer, and Revision 4 to Enstrom Service Directive Bulletin No. 0110, dated January 23, 2012 (SDB 0110), for Model F–28C, F–28C–2, F– 28F, 280C, 280F, and 280FX helicopters. In its comment, the manufacturer stated that the list of affected part numbers for the F–28 series and 280 series helicopter should include P/N KUP14D55–24 and that this P/N was erroneously left off of Enstrom’s original Service Directive Bulletin. It stated that the same safety concerns also exist with this relay and that adding this P/N will not affect the cost analysis or fleet size as these aircraft were included in the initial calculations. We agree with the commenter that the additional part numbered relay contained in Enstrom SDB 0110 should be added to the applicability section of the AD because it may contain the same unsafe condition. Also, we agree that the revised compliance instructions contained in SDB 0110 should be required. PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 FAA’s Determination We are issuing this AD because we evaluated all the relevant information, including the comment received and the revised service information, and determined the unsafe condition described previously is likely to exist or develop in other helicopters of these same type designs. Related Service Information We reviewed Enstrom SDB No. T– 039, Revision 3, dated July 6, 2011 (SDB T–039), for Model TH–28, 480, and 480B helicopters and Enstrom SDB 0110, for Model F–28C, F–28C–2, F– 28F, 280C, 280F, and 280FX helicopters. SDB T–039 specifies, for helicopters with a trim relay, P/N M83536/10– 024M, procedures for modifying the lateral and longitudinal trim actuator assembly using the cyclic trim assembly kit (modification kit), P/N 4230045–1, and specifies performing an operational check and flight test to determine if the trim is operating correctly after the modification. SDB 0110 specifies, for helicopters with a trim relay, P/N KUP14D55–24, KUP14D55–472, M83536/10–015M, or M83536/10– 024M, procedures for modifying the lateral and longitudinal trim actuator assembly using the modification kit, P/N 28–01063–1, and specifies performing an operational check and flight test to determine if the trim is operating correctly after the modification. The SDBs state that the modification kits contain the upgraded bracket. AD Requirements In addition to those part-numbered trim relays contained in the applicability section of the current AD 2011–26–10, this AD adds trim relay P/N KUP14D55–24. Also, this AD adopts the revised modification instructions for the Model F–28C, F– 28C–2, F–28F, 280C, 280F, and 280FX helicopters contained in SDB 0110. Otherwise, this AD retains most of the requirements of AD 2011–26–10, which requires modifying the lateral and longitudinal trim actuator assembly, using modification kit, P/N 28–01063–1, for the Model F–28C, F–28C–2, F–28F, 280C, 280F, and 280FX helicopters and modification kit, P/N 4230045–1, for the Model TH–28, 480, and 480B helicopters, and verifying that the modification has been completed properly by performing an operational and flight test after the modification is complete. The actions required by this AD are to be accomplished by following specified E:\FR\FM\18JNR1.SGM 18JNR1 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations portions of the SDBs described previously. Differences Between This AD and the Service Information The SDBs specify, before further flight, to insert a special addendum into the Emergency Procedures section of the Flight Manual, and this AD does not require this action. Costs of Compliance We estimate that this AD will affect 207 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. For Model 480, 480B, and TH–28, modifying the actuator assemblies will require 8 work hours at a cost of $85 per hour and parts will cost $327; the cost per helicopter will be $1,007. For Model 280C, 280F, 280FX, F–28C, F–28C–2, and F–28F, modifying the actuator assemblies will require 8 work hours at a cost of $85 per hour; parts will cost $383; and the cost per helicopter will be $1,063. srobinson on DSK4SPTVN1PROD with RULES FAA’s Justification and Determination of the Effective Date Providing an opportunity for public comments prior to 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 prior to the adoption of this rule because the required corrective actions must be accomplished within 5 hours time-in-service, a very short time period based on the average flight-hour utilization rate of these helicopters. 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 contrary to the public interest 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 VerDate Mar<15>2010 16:18 Jun 15, 2012 Jkt 226001 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 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 removing Amendment 39–16900 (77 FR 729, January 6, 2012), and adding the following new airworthiness directive (AD): ■ 2012–11–05 Enstrom Helicopter Corporation: Amendment 39–17068; Docket No. FAA–2012–0562; Directorate Identifier 2012–SW–038–AD. (a) Applicability This AD applies to the Enstrom Model F–28C, F–28C–2, F–28F, 280C, 280F, 280FX, PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 36133 TH–28, 480, and 480B helicopters with a trim relay, part-number (P/N) KUP14D55–24, KUP14D55–472, M83536/10–015M, or M83536/10–024M, certificated in any category. Note to paragraph (a) of this AD: This AD does not apply to the specified helicopters with a reversible trim motor, P/N 28–16621 (Ford Motor Company C1AZ–14553A) or P/ N AD1R–10 (Signal Electric). (b) Unsafe Condition This AD defines the unsafe condition as a failure of a trim relay in the cyclic trim system. This condition could result in reduced controllability of the helicopter and subsequent loss of control of the helicopter. (c) Other Affected ADs This AD supersedes AD 2011–26–10, Amendment 39–16900 (77 FR 729, January 6, 2012). (d) Effective Date This AD becomes effective July 3, 2012. (e) 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. (f) Required Actions Within 5 hours time-in-service (TIS) or at the next annual or 100 hour TIS inspection, whichever occurs first: (1) For the Enstrom Model F–28C, F–28C– 2, F–28F, 280C, 280F, and 280FX helicopters, modify the lateral and longitudinal trim actuator assemblies using the cyclic trim assembly kit (modification kit), P/N 28– 01063–1, in accordance with the instructions in paragraph 6.1 of the Enstrom Service Directive Bulletin (SDB) No. 0110, Revision 4, dated January 23, 2012 (SDB No. 0110 R4), except when the instructions specify using ‘‘Aeroshell 22 grease’’ or ‘‘VC–3 Vibra-tite thread locker,’’ you may use an equivalent product. (2) For the Enstrom Model TH–28, 480, and 480B helicopters, modify the lateral and longitudinal trim actuator assemblies using the modification kit, P/N 4230045–1, in accordance with the instructions in paragraph 6.1 of the Enstrom SDB No. T–039, Revision 3, dated July 6, 2011 (SDB No. T–039 R3), except when the instructions specify using ‘‘Aeroshell 22 grease’’ or ‘‘VC– 3 Vibra-tite thread locker,’’ you may use an equivalent product, and you are not required to contact Enstrom Customer Service. (3) After modifying the lateral and longitudinal trim actuator assemblies in accordance with paragraphs (f)(1) or (f)(2) of this AD, before further flight, operationally test the trim limits in accordance with paragraph 6.2. of the SDB for your model helicopter, and determine during a flight test whether there is appropriate trim authority in accordance with paragraph 6.3. of the SDB for your model helicopter. (g) Special Flight Permits A one-time special-flight permit may be issued in accordance with 14 CFR 21.197 and 21.199 provided the helicopter is operated with the trim system circuit breaker pulled. E:\FR\FM\18JNR1.SGM 18JNR1 36134 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations (h) Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (1) The Manager, Chicago Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Gregory J. Michalik, Enstrom Program Manager, FAA, Chicago Aircraft Certification Office, 2300 East Devon Avenue, Room 107, Des Plaines, Illinois, 60018; telephone (847) 294–7135; fax (847) 294–7834; email: gregory.michalik@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. Federal Aviation Administration (i) Subject Joint Aircraft Service Component (JASC) Code: 6710: Main Rotor Control. (j) Material Incorporated by Reference srobinson on DSK4SPTVN1PROD with RULES (1) 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 51. (2) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on July 3, 2012. (i) Enstrom Service Directive Bulletin No. 0110, Revision 4, dated January 23, 2012, for Model F–28C, F–28C–2, F–28F, 280C, 280F, and 280FX helicopters. (4) The following service information was approved for IBR on January 23, 2012 (77 FR 729, January 6, 2012). (i) Enstrom Service Directive Bulletin No. T–039, Revision 3, dated July 6, 2011, for Model TH–28, 480, and 480B helicopters. (5) For service information identified in this AD, contact Enstrom Helicopter Corporation, 2209 22nd St., Menominee, Michigan, 49858–0490; telephone: 906–863– 1200; email: customerservice@ enstromhelicopter.com; Web site: https:// www.enstromhelicopter.com/enstrom_new/ enstrom_support_tec.html. (6) 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 or 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 May 17, 2012. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2012–14634 Filed 6–15–12; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 16:18 Jun 15, 2012 Jkt 226001 14 CFR Part 39 [Docket No. FAA–2011–1254; Directorate Identifier 2010–NM–178–AD; Amendment 39–17083; AD 2012–12–04] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 737–300, –400, and –500 series airplanes. That AD currently requires repetitive external detailed inspections or non-destructive inspections to detect cracks in the fuselage skin along the chem-mill steps at stringers S–1 and S– 2R, between station (STA) 400 and STA 460, and repair if necessary. This new AD adds inspections for cracking in additional fuselage skin locations, and repair if necessary. This new AD also reduces the inspection thresholds and repetitive intervals for certain airplanes. This AD was prompted by reports of additional crack findings of the fuselage skin at the chem-mill steps. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin panels at the chem-mill steps, which could result in sudden fracture and failure of the fuselage skin panels, and consequent rapid decompression of the airplane. DATES: This AD is effective July 23, 2012. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of July 23, 2012. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced 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. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at https:// PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425– 917–6447; fax: 425–917–6590; email: wayne.lockett@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2008–19–03, Amendment 39–15670 (73 FR 56958, October 1, 2008). That AD applies to the specified products. The NPRM published in the Federal Register on November 28, 2011 (76 FR 72853). That NPRM proposed to continue to require repetitive external detailed inspections or non-destructive inspections to detect cracks in the fuselage skin along the chem-mill steps at stringers S–1 and S– 2R, between station (STA) 400 and STA 460, and repair if necessary. That NPRM also proposed to add inspections for cracking in additional fuselage skin locations, and repair if necessary. That NPRM also proposed to reduce the inspection thresholds and repetitive intervals for certain airplanes. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (76 FR 72853, November 28, 2011) and the FAA’s response to each comment. Support for the NPRM (76 FR 72853, November 28, 2011) The National Transportation Board supports the NPRM (76 FR 72853, November 28, 2011). Request To Revise Paragraph (j) of the NPRM (76 FR 72853, November 28, 2011) Boeing asked that we include Boeing Alert Service Bulletin 737–53A1293, Revision 1, dated July 7, 2010, in the exception to the service bulletin E:\FR\FM\18JNR1.SGM 18JNR1

Agencies

[Federal Register Volume 77, Number 117 (Monday, June 18, 2012)]
[Rules and Regulations]
[Pages 36131-36134]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-14634]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0562; Directorate Identifier 2012-SW-038-AD; 
Amendment 39-17068; AD 2012-11-05]
RIN 2120-AA64


Airworthiness Directives; Enstrom Helicopter Corporation 
Helicopters

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

ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for Enstrom Helicopter Corporation (Enstrom) Model F-28C, F-28C-2, F-
28F, 280C, 280F, 280FX, TH-28, 480, and 480B helicopters to add another 
trim relay to the applicability and to revise the modification 
instructions. This AD is prompted by the discovery that another part-
numbered trim relay, inadvertently omitted from the current AD, may 
contain the same unsafe condition. These actions are intended to 
prevent failure of the cyclic trim system and subsequent loss of 
control of the helicopter.

DATES: This AD becomes effective July 3, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 3, 
2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
January 23, 2012 (77 FR 729, January 6, 2012).
    We must receive comments on this AD by August 17, 2012.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to https://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

[[Page 36132]]

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 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, 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 Enstrom 
Helicopter Corporation, 2209 22nd St., Menominee, Michigan, 49858-0490; 
telephone: 906-863-1200; email: customerservice@enstromhelicopter.com; 
Web site: https://www.enstromhelicopter.com/enstrom_new/enstrom_support_tec.html. 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.

FOR FURTHER INFORMATION CONTACT: Gregory J. Michalik, Enstrom Program 
Manager, FAA, Chicago Aircraft Certification Office, 2300 East Devon 
Avenue, Room 107, Des Plaines, Illinois, 60018; telephone (847) 294-
7135; email: gregory.michalik@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

    On December 14, 2011, we issued AD 2011-26-10, amendment 39-16900 
(77 FR 729, January 6, 2012) for Enstrom Model F-28C, F-28C-2, F-28F, 
280C, 280F, 280FX, TH-28, 480, and 480B helicopters with a trim relay, 
part-number (P/N) KUP14D55-472, M83536/10-015M, or M83536/10-024M. That 
AD requires modifying the lateral and longitudinal trim actuator 
assemblies by replacing the actuator and limit switch bracket to 
provide a positive stop for the trim actuator. In the event of a trim 
actuator runaway, the new bracket will stop the actuator, causing the 
circuit breaker to trip before any significant loss of control occurs. 
After the trim actuator assemblies are modified, that AD requires 
performing operational (ground) and flight tests to determine that the 
trim relay is working correctly. That AD was prompted by reports of 4 
failures in the cyclic trim system in the field, 2 that occurred on the 
Enstrom Model 480B helicopter and 2 that occurred on the Enstrom Model 
F28 helicopter. These failures resulted in reduced controllability of 
the helicopter. We issued that AD to prevent failure of the cyclic trim 
system and subsequent loss of control of the helicopter.

Comments

    Since we issued immediately adopted AD 2011-26-10, we received one 
comment from Enstrom, the manufacturer, and Revision 4 to Enstrom 
Service Directive Bulletin No. 0110, dated January 23, 2012 (SDB 0110), 
for Model F-28C, F-28C-2, F-28F, 280C, 280F, and 280FX helicopters. In 
its comment, the manufacturer stated that the list of affected part 
numbers for the F-28 series and 280 series helicopter should include P/
N KUP14D55-24 and that this P/N was erroneously left off of Enstrom's 
original Service Directive Bulletin. It stated that the same safety 
concerns also exist with this relay and that adding this P/N will not 
affect the cost analysis or fleet size as these aircraft were included 
in the initial calculations.
    We agree with the commenter that the additional part numbered relay 
contained in Enstrom SDB 0110 should be added to the applicability 
section of the AD because it may contain the same unsafe condition. 
Also, we agree that the revised compliance instructions contained in 
SDB 0110 should be required.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information, including the comment received and the revised service 
information, and determined the unsafe condition described previously 
is likely to exist or develop in other helicopters of these same type 
designs.

Related Service Information

    We reviewed Enstrom SDB No. T-039, Revision 3, dated July 6, 2011 
(SDB T-039), for Model TH-28, 480, and 480B helicopters and Enstrom SDB 
0110, for Model F-28C, F-28C-2, F-28F, 280C, 280F, and 280FX 
helicopters. SDB T-039 specifies, for helicopters with a trim relay, P/
N M83536/10-024M, procedures for modifying the lateral and longitudinal 
trim actuator assembly using the cyclic trim assembly kit (modification 
kit), P/N 4230045-1, and specifies performing an operational check and 
flight test to determine if the trim is operating correctly after the 
modification. SDB 0110 specifies, for helicopters with a trim relay, P/
N KUP14D55-24, KUP14D55-472, M83536/10-015M, or M83536/10-024M, 
procedures for modifying the lateral and longitudinal trim actuator 
assembly using the modification kit, P/N 28-01063-1, and specifies 
performing an operational check and flight test to determine if the 
trim is operating correctly after the modification. The SDBs state that 
the modification kits contain the upgraded bracket.

AD Requirements

    In addition to those part-numbered trim relays contained in the 
applicability section of the current AD 2011-26-10, this AD adds trim 
relay P/N KUP14D55-24. Also, this AD adopts the revised modification 
instructions for the Model F-28C, F-28C-2, F-28F, 280C, 280F, and 280FX 
helicopters contained in SDB 0110. Otherwise, this AD retains most of 
the requirements of AD 2011-26-10, which requires modifying the lateral 
and longitudinal trim actuator assembly, using modification kit, P/N 
28-01063-1, for the Model F-28C, F-28C-2, F-28F, 280C, 280F, and 280FX 
helicopters and modification kit, P/N 4230045-1, for the Model TH-28, 
480, and 480B helicopters, and verifying that the modification has been 
completed properly by performing an operational and flight test after 
the modification is complete.
    The actions required by this AD are to be accomplished by following 
specified

[[Page 36133]]

portions of the SDBs described previously.

Differences Between This AD and the Service Information

    The SDBs specify, before further flight, to insert a special 
addendum into the Emergency Procedures section of the Flight Manual, 
and this AD does not require this action.

Costs of Compliance

    We estimate that this AD will affect 207 helicopters of U.S. 
Registry. We estimate that operators may incur the following costs in 
order to comply with this AD. For Model 480, 480B, and TH-28, modifying 
the actuator assemblies will require 8 work hours at a cost of $85 per 
hour and parts will cost $327; the cost per helicopter will be $1,007. 
For Model 280C, 280F, 280FX, F-28C, F-28C-2, and F-28F, modifying the 
actuator assemblies will require 8 work hours at a cost of $85 per 
hour; parts will cost $383; and the cost per helicopter will be $1,063.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments prior to 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 
prior to the adoption of this rule because the required corrective 
actions must be accomplished within 5 hours time-in-service, a very 
short time period based on the average flight-hour utilization rate of 
these helicopters.
    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 contrary to 
the public interest 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 removing Amendment 39-16900 (77 FR 
729, January 6, 2012), and adding the following new airworthiness 
directive (AD):

2012-11-05 Enstrom Helicopter Corporation: Amendment 39-17068; 
Docket No. FAA-2012-0562; Directorate Identifier 2012-SW-038-AD.

(a) Applicability

    This AD applies to the Enstrom Model F-28C, F-28C-2, F-28F, 
280C, 280F, 280FX, TH-28, 480, and 480B helicopters with a trim 
relay, part-number (P/N) KUP14D55-24, KUP14D55-472, M83536/10-015M, 
or M83536/10-024M, certificated in any category.
    Note to paragraph (a) of this AD: This AD does not apply to the 
specified helicopters with a reversible trim motor, P/N 28-16621 
(Ford Motor Company C1AZ-14553A) or P/N AD1R-10 (Signal Electric).

(b) Unsafe Condition

    This AD defines the unsafe condition as a failure of a trim 
relay in the cyclic trim system. This condition could result in 
reduced controllability of the helicopter and subsequent loss of 
control of the helicopter.

(c) Other Affected ADs

    This AD supersedes AD 2011-26-10, Amendment 39-16900 (77 FR 729, 
January 6, 2012).

(d) Effective Date

    This AD becomes effective July 3, 2012.

(e) 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.

(f) Required Actions

    Within 5 hours time-in-service (TIS) or at the next annual or 
100 hour TIS inspection, whichever occurs first:
    (1) For the Enstrom Model F-28C, F-28C-2, F-28F, 280C, 280F, and 
280FX helicopters, modify the lateral and longitudinal trim actuator 
assemblies using the cyclic trim assembly kit (modification kit), P/
N 28-01063-1, in accordance with the instructions in paragraph 6.1 
of the Enstrom Service Directive Bulletin (SDB) No. 0110, Revision 
4, dated January 23, 2012 (SDB No. 0110 R4), except when the 
instructions specify using ``Aeroshell 22 grease'' or ``VC-3 Vibra-
tite thread locker,'' you may use an equivalent product.
    (2) For the Enstrom Model TH-28, 480, and 480B helicopters, 
modify the lateral and longitudinal trim actuator assemblies using 
the modification kit, P/N 4230045-1, in accordance with the 
instructions in paragraph 6.1 of the Enstrom SDB No. T-039, Revision 
3, dated July 6, 2011 (SDB No. T-039 R3), except when the 
instructions specify using ``Aeroshell 22 grease'' or ``VC-3 Vibra-
tite thread locker,'' you may use an equivalent product, and you are 
not required to contact Enstrom Customer Service.
    (3) After modifying the lateral and longitudinal trim actuator 
assemblies in accordance with paragraphs (f)(1) or (f)(2) of this 
AD, before further flight, operationally test the trim limits in 
accordance with paragraph 6.2. of the SDB for your model helicopter, 
and determine during a flight test whether there is appropriate trim 
authority in accordance with paragraph 6.3. of the SDB for your 
model helicopter.

(g) Special Flight Permits

    A one-time special-flight permit may be issued in accordance 
with 14 CFR 21.197 and 21.199 provided the helicopter is operated 
with the trim system circuit breaker pulled.

[[Page 36134]]

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Chicago Aircraft Certification Office, FAA, may 
approve AMOCs for this AD. Send your proposal to: Gregory J. 
Michalik, Enstrom Program Manager, FAA, Chicago Aircraft 
Certification Office, 2300 East Devon Avenue, Room 107, Des Plaines, 
Illinois, 60018; telephone (847) 294-7135; fax (847) 294-7834; 
email: gregory.michalik@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.

 (i) Subject

    Joint Aircraft Service Component (JASC) Code: 6710: Main Rotor 
Control.

 (j) Material Incorporated by Reference

    (1) 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 51.
    (2) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
July 3, 2012.
    (i) Enstrom Service Directive Bulletin No. 0110, Revision 4, 
dated January 23, 2012, for Model F-28C, F-28C-2, F-28F, 280C, 280F, 
and 280FX helicopters.
    (4) The following service information was approved for IBR on 
January 23, 2012 (77 FR 729, January 6, 2012).
    (i) Enstrom Service Directive Bulletin No. T-039, Revision 3, 
dated July 6, 2011, for Model TH-28, 480, and 480B helicopters.
    (5) For service information identified in this AD, contact 
Enstrom Helicopter Corporation, 2209 22nd St., Menominee, Michigan, 
49858-0490; telephone: 906-863-1200; email: 
customerservice@enstromhelicopter.com; Web site: https://www.enstromhelicopter.com/enstrom_new/enstrom_support_tec.html.
    (6) 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 or 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 May 17, 2012.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-14634 Filed 6-15-12; 8:45 am]
BILLING CODE 4910-13-P
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