Airworthiness Directives; Eurocopter France (Eurocopter) Model EC130 B4 Helicopters, 15802-15805 [2011-6212]

Download as PDF 15802 Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations Alternative Methods of Compliance (AMOCs) PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2011–06–12 The Boeing Company: Amendment 39–16637; Docket No. FAA–2010–1202; Directorate Identifier 2010–NM–167–AD. Effective Date (a) This AD is effective April 26, 2011. Affected ADs (b) None. Applicability (c) This AD applies to all The Boeing Company Model MD–90–30 airplanes, certificated in any category. Subject (d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 55, Stabilizers. Unsafe Condition (e) This AD was prompted by a report of a crack found in the upper center skin panel at the aft inboard corner of a right horizontal stabilizer. We are issuing this AD to detect and correct cracks in the upper center skin panel of the horizontal stabilizer. Uncorrected cracks might ultimately lead to the loss of overall structural integrity of the horizontal stabilizer. Emcdonald on DSK2BSOYB1PROD with RULES Compliance (f) Comply with this AD within the compliance times specified, unless already done. Inspections (g) Before the accumulation of 20,000 total flight cycles, or within 3,778 flight cycles after the effective date of this AD, whichever occurs later, do eddy current inspections to detect cracking of the left and right upper center skin panels of the horizontal stabilizer, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90–55A015, dated July 16, 2010. (1) If no crack is found during any inspection required by paragraph (g) of this AD, repeat the applicable inspections thereafter at the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin MD90–55A015, dated July 16, 2010. (2) If any crack is found during any inspection required by paragraph (g) of this AD, before further flight, replace the skin panel with a serviceable skin panel, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90–55A015, dated July 16, 2010. Within 20,000 flight cycles after the replacement, do eddy current inspections as required by paragraph (g) of this AD. VerDate Mar<15>2010 16:40 Mar 21, 2011 Jkt 223001 (h)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. (2) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD. Issued in Renton, Washington, on March 9, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–6249 Filed 3–21–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0212; Directorate Identifier 2010–SW–055–AD; Amendment 39–16632; AD 2011–06–07] RIN 2120–AA64 Airworthiness Directives; Eurocopter France (Eurocopter) Model EC130 B4 Helicopters Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. AGENCY: This amendment adopts a new airworthiness directive (AD) for (i) For more information about this AD, Eurocopter Model EC130 B4 helicopters. contact Roger Durbin, Aerospace Engineer, This action requires identifying and Los Angeles ACO, Airframe Branch, ANM– inspecting a certain emergency flotation 120L, FAA, 3960 Paramount Boulevard, gear unit ‘‘1G’’ (1G unit). This action also Lakewood, CA 90712–4137; phone: 562–627– requires modification of certain affected 5233; fax: 562–627–5210; e-mail: 1G units. This amendment is prompted Roger.Durbin@faa.gov. by an uncommanded in-flight Material Incorporated by Reference deployment of the emergency flotation (j) You must use Boeing Alert Service gear when it was not armed by the crew. Bulletin MD90–55A015, dated July 16, 2010, The actions specified in this AD are to do the actions required by this AD, unless intended to prevent an uncommanded the AD specifies otherwise. in-flight deployment of the emergency (1) The Director of the Federal Register flotation gear, unexpected deceleration approved the incorporation by reference of and pitch down movement of the Boeing Alert Service Bulletin MD90–55A015, helicopter, and subsequent loss of dated July 16, 2010, under 5 U.S.C. 552(a) control of the helicopter. and 1 CFR part 51. DATES: Effective April 6, 2011. (2) For service information identified in The incorporation by reference of this AD, contact Boeing Commercial certain publications listed in the Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC regulations is approved by the Director of the Federal Register as of April 6, D800–0019, Long Beach, California 90846– 0001; phone: 206–544–5000, extension 2; fax: 2011. 206–766–5683; e-mail: Comments for inclusion in the Rules dse.boecom@boeing.com; Internet: https:// Docket must be received on or before www.myboeingfleet.com. May 23, 2011. (3) You may review copies of the service ADDRESSES: Use one of the following information at the FAA, Transport Airplane addresses to submit comments on this Directorate, 1601 Lind Avenue, SW., Renton, AD: Washington. For information on the • Federal eRulemaking Portal: Go to availability of this material at the FAA, call https://www.regulations.gov. Follow the 425–227–1221. instructions for submitting comments. (4) You may also review copies of the • Fax: 202–493–2251. service information that is incorporated by • Mail: U.S. Department of reference at the National Archives and Transportation, Docket Operations, M– Records Administration (NARA). For 30, West Building Ground Floor, Room information on the availability of this W12–140, 1200 New Jersey Avenue, SE., material at an NARA facility, call 202–741– Washington, DC 20590. 6030, or go to https://www.archives.gov/ • Hand Delivery: U.S. Department of federal_register/code_of_federal_regulations/ Transportation, Docket Operations, M– ibr_locations.html. SUMMARY: Related Information PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\22MRR1.SGM 22MRR1 Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this AD from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 75053–4005, telephone (800) 232–0323, fax (972) 641–3710, or at https:// www.eurocopter.com. Examining the Docket You may examine the docket that contains the AD, any comments, and other information 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 Docket Operations office (telephone (800) 647–5527) is located in Room W12–140 on the ground floor of the West Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: George Schwab, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety Management Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–5114, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: Emcdonald on DSK2BSOYB1PROD with RULES Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD No. 2010–0088–E, dated May 6, 2010, to correct an unsafe condition for the Model EC130 B4 helicopters. EASA advises that an uncontrolled in-flight deployment of the emergency flotation gear (not armed) on an EC130 B4 helicopter has been reported. The flight crew heard a detonation followed by heavy vibrations and noticed the emergency flotation gear floats were inflating. Investigations on the emergency flotation gear control system revealed that a wire was damaged inside the 1G unit. This wire was damaged, due to interference with the screw securing cable 1GR19E lug to the bus bar, causing a short circuit in the emergency flotation gear deployment activation circuit and the consequent deployment of the emergency flotation gear. EASA further states the possibility of interference of the 1G unit’s internal wire harnesses with a fuselage metal structure member (stringer) has been identified, which could have the same consequences. VerDate Mar<15>2010 16:40 Mar 21, 2011 Jkt 223001 Related Service Information Eurocopter has issued Emergency Alert Service Bulletin No. 25A037, dated April 27, 2010, for the Model EC130 B4 helicopters, which specifies inspecting 1G units without an ‘‘*’’ displayed on the 1G unit panel after the part number (P/N) and taking various corrective actions at various times pending installation of a conforming 1G unit. EASA classified this EASB as mandatory and issued AD No. 2010– 0088–E, dated May 6, 2010, to ensure the continued airworthiness of these helicopters. FAA’s Evaluation and Unsafe Condition Determination This helicopter has been approved by the aviation authority of France and is approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, their technical representative, has notified us of the unsafe condition described in the MCAI AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of this same type design. Differences Between This AD and the EASA AD This AD does not require the actions to be completed at the compliance times of 3 months and 8 months, nor does it require the repetitive actions specified in the EASA AD. This AD requires the actions to be done within 15 hours timein-service (TIS). Also, this AD refers to flight hours as hours TIS. FAA’s Determination and Requirements of This AD This unsafe condition is likely to exist or develop on other helicopters of the same type design. Therefore, this AD is being issued to prevent an uncommanded in-flight deployment of the emergency flotation gear, unexpected deceleration and pitch down movement of the helicopter, and subsequent loss of control of the helicopter. This AD requires determining if the 1G unit has an asterisk after the P/N displayed on the 1G unit panel. If an asterisk follows the P/N, the AD requires inspecting for a rubber extrusion installed on the stringer. If no rubber extrusion is installed on the stringer, the AD requires removing the 1G unit, bonding a rubber extrusion on the stringer, reinstalling the 1G unit, and functionally testing the emergency flotation gear control system. If no asterisk follows the P/N, the AD requires removing the 1G unit and PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 15803 inspecting the 1G unit for interference between the harness wires and the stringer and between internal parts. Also, the AD requires if no rubber extrusion is installed on the stringer, protecting the stringer by bonding a rubber extrusion on the stringer. The AD also requires inspecting for interference between the attachment screw and the wires of the nearby harness and for damage to the wires of the harness. The AD also requires modifying the 1G unit as necessary to protect the 1G unit from interference. Also, the AD requires identifying the modified 1G unit by marking an asterisk after the P/N. The AD also requires reinstalling and functionally testing the 1G unit. Installing a conforming 1G unit is terminating action for the requirements of this AD. Do the actions by following specified portions of the service bulletin described previously. The short compliance time involved is required because the previously described critical unsafe condition can adversely affect the controllability of the helicopter. This AD requires, within 15 hours TIS, determining whether a conforming 1G unit is installed, and if not, modifying the 1G unit within 15 hours TIS. Fifteen hours TIS is a very short compliance time; therefore, this AD must be issued immediately. Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days. Costs of Compliance We estimate that this AD will affect about 119 helicopters of U.S. registry. Determining whether an asterisk is present on the 1G unit panel will require a minimal amount of time. We estimate that it will take about 8 workhours per helicopter to remove, modify, and replace a 1G unit. The average labor rate is $85 per work-hour. Required parts will cost about $25 per helicopter. Based on these figures, we estimate the cost of this AD on U.S. operators is $8,460, assuming 12 helicopters will require modification of the 1G unit per this AD. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES. Include ‘‘Docket No. FAA–2011–0212; E:\FR\FM\22MRR1.SGM 22MRR1 15804 Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations Directorate Identifier 2010–SW–055– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Using the search function of the docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent the comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). Emcdonald on DSK2BSOYB1PROD with RULES Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared an economic evaluation of the estimated costs to comply with this AD. See the AD docket to examine the economic evaluation. 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 VerDate Mar<15>2010 16:40 Mar 21, 2011 Jkt 223001 the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, 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. Section 39.13 is amended by adding a new airworthiness directive to read as follows: ■ 2011–06–07 Eurocopter France: Amendment 39–16632; Docket No. FAA–2011–0212; Directorate Identifier 2010–SW–055–AD. Applicability: Model EC130 B4 helicopters with a flotation gear unit ‘‘1G’’ (1G unit), part number (P/N) 350A63256300, installed, certificated in any category. Compliance: Within 15 hours time-inservice, unless accomplished previously. To prevent an uncommanded in-flight deployment of the emergency flotation gear, unexpected deceleration and pitch down movement of the helicopter, and subsequent loss of control of the helicopter, do the following: (a) Determine whether the 1G unit has an asterisk (*) after the P/N displayed on the 1G unit panel as shown in Figure 4 of Eurocopter Emergency Alert Service Bulletin No. 25A037, dated April 27, 2010 (EASB). (b) If there is an asterisk after the P/N displayed on the 1G unit panel, determine if there is a rubber extrusion installed on the stringer as shown in Figure 6 of the EASB. (1) If no rubber extrusion is installed on the stringer, remove the 1G unit by following the Accomplishment Instructions, paragraph 2.B.2.a. of the EASB. (2) Bond a rubber extrusion onto the stringer using Bostik 1400 or an equivalent adhesive. Bostik 1400 is ready for use; if using an equivalent adhesive, follow the manufacturer’s directions for preparation and application. (i) Thoroughly clean the bonding surfaces of the stringer; remove all traces of grease. (ii) Apply a uniform adhesive film on the bonding surfaces. (A) For Bostik 1400, allow to dry until tack free (about 15 minutes). (B) For equivalent adhesive, follow the manufacturer’s procedures. PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 (iii) After adhesive application, assemble the bonding faces and press firmly to eliminate air bubbles. Maintain the pressure throughout the hardening period as described for the adhesive being used. For Bostik 1400, the adhesive hardens in about 48 hours at room temperature. (3) Reinstall the 1G unit by following the Accomplishment Instructions, paragraph 2.B.2.b., of the EASB. Functionally test the emergency flotation gear control system. (c) If there is no asterisk displayed after the P/N on the 1G unit panel, remove the 1G unit by following the Accomplishment Instructions, paragraph 2.B.2.a., of the EASB. (1) Inspect the 1G unit for interference: (i) If you find interference between the harness wires and the stringer, install a sheath, P/N EN6049–006–08–5, on all the harnesses in the area of the interference, and secure the sheath with cable ties as depicted in Figure 5 of the EASB. (ii) If you find interference between the harness wires and the inside surface of the 1G unit or with any of the 1G unit’s internal components, remove the installed cable ties, P/N E0043–1A0P, and spacer(s), P/N E0688– 01, as required, to allow repositioning or routing of the harness to eliminate interference. Secure repositioned harnesses using new cable ties, P/N E0043–1A0P, and new spacers, P/N E0688–01. (iii) If you find interference between the harness and the helicopter structural stringer, install a sheath, P/N EN6049–006–08–5, on all the harnesses located at the stringer as depicted in Figures 5 and 6 of the EASB. Secure the sheath with cable ties, P/N E0043–1A0P, so that no interference between the sheathed harness and the structural stringer exists. (iv) Bond a black rubber extrusion, P/N BT4, on the stringer as shown in Figure 6 by following the requirements of paragraph (b)(2) of this AD. (2) Inspect the attachment screw of cable 1GR19E for orientation and arrangement that matches the Post EASB detail, as shown in insert D of Figure 5 of the EASB, and determine if it is covered with heat shrink, P/N VG95343T05E004A, or equivalent. If orientation and arrangement of the attachment screw cable 1GR19E are not as shown in insert D of Figure 5 or the attachment screw is not covered with heat shrink, modify the attachment screw by following the Accomplishment Instructions, paragraph 2.B.5.b., of the EASB. Note 1. Figure 5 of the EASB does not show the heat shrink installed for clarity of screw head and lug detail. (3) Inspect for damage to a wire of the harness inside the 1G unit as depicted in Figure 7 of the EASB. Replace any damaged wire using the correct wire and contact information listed in the Appendix, paragraph 4, of the EASB. (4) Mark an asterisk ‘‘*’’ after P/N 350A63256300 on the 1G unit panel using indelible ink to indicate compliance with this AD. (5) Reinstall the 1G unit by following the Accomplishment Instructions, paragraph 2.B.2.b., of the EASB, and functionally test the emergency flotation gear control system. (d) Installing an airworthy 1G unit that has been modified and identified as required by E:\FR\FM\22MRR1.SGM 22MRR1 Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations this AD is terminating action for the requirements of this AD. (e) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Safety Management Group, FAA, Attn: George Schwab, Aviation Safety Engineer, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222– 5114, fax (817) 222–5961, for information about previously approved alternative methods of compliance. (f) The Joint Aircraft System/Component (JASC) Code is 2497: Electrical Power System Wiring. (g) Remove and install the 1G unit, determine the correct wire and contact information, and do the inspections by following the specified portions of Eurocopter Emergency Alert Service Bulletin No. 25A037, dated April 27, 2010. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 75053–4005, telephone (800) 232–0323, fax (972) 641–3710, or at https://www.eurocopter.com. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas, 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. (h) This amendment becomes effective on April 6, 2011. Note 2: The subject of this AD is addressed in European Aviation Safety Agency No. 2010–0088–E, dated May 6, 2010. ACTION: Final rule. We are superseding an existing airworthiness directive (AD) that applies to the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: Prompted by a reported in-service event, EASA issued AD 2009–0084 to prevent unwanted movement of pilot- or co-pilot seat in the horizontal direction which is considered as potentially unsafe, especially during the takeoff phase when the speed of the aeroplane is greater than 100 knots and until landing gear retraction. [Docket No. FAA–2010–1162; Directorate Identifier 2010–NM–099–AD; Amendment 39–16634; AD 2011–06–09] * * * * * Uncommanded movement of the pilot and co-pilot seats during takeoff or landing could interfere with the operation of the airplane and, as a result, could cause loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective April 26, 2011. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of April 26, 2011. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of June 12, 2009 (74 FR 25399, May 28, 2009). ADDRESSES: 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. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; phone: 425– 227–2125; fax: 425–227–1149. SUPPLEMENTARY INFORMATION: RIN 2120–AA64 Discussion Issued in Fort Worth, Texas, March 7, 2011. Lance T. Gant, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2011–6212 Filed 3–21–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Emcdonald on DSK2BSOYB1PROD with RULES 14 CFR Part 39 Airworthiness Directives; Airbus Model A310 Series Airplanes, and Airbus Model A300 B4–600, B4–600R, and F4– 600R Series Airplanes, and Model C4– 605R Variant F Airplanes (Collectively Called A300–600 Series Airplanes) Federal Aviation Administration (FAA), Department of Transportation (DOT). AGENCY: VerDate Mar<15>2010 16:40 Mar 21, 2011 Jkt 223001 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 December 1, 2010 (75 FR 74665), and proposed to supersede AD 2009–11–09, Amendment 39–15919 (74 FR 25399, May 28, 2009). That NPRM proposed to correct an unsafe condition PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 15805 for the specified products. The MCAI states: Prompted by a reported in-service event, EASA issued AD 2009–0084 [which corresponds to FAA AD 2009–11–09] to prevent unwanted movement of pilot- or copilot seat in the horizontal direction which is considered as potentially unsafe, especially during the takeoff phase when the speed of the aeroplane is greater than 100 knots and until landing gear retraction. AD 2009–0084 required the deactivation of the electrical power of SOGERMA pilot seats P/N 2510112 series and co-pilot seats P/N 2510113 series. Optional intermediate actions were also provided by AD 2009–0084 to allow partial or full restoration of seat adjustment functionality. Since AD 2009–0084 was issued, a permanent solution has been developed that terminates the de-activation requirement and invalidates the intermediate actions. Consequently, this AD retains requirements of EASA AD 2009–0084, which is superseded, and requires implementing the terminating action. In addition, this AD prohibits the (re)installation of unmodified pilot- and co-pilot seats on any aeroplane that has been modified in accordance with the requirements of this AD. Uncommanded movement of the pilot and co-pilot seats during takeoff or landing could interfere with the operation of the airplane and, as a result, could cause loss of control of the airplane. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Since issuance of the NPRM, Airbus has issued Mandatory Service Bulletin A310–25–2205, Revision 01, dated November 19, 2010. This revision does not require any additional work. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. We have updated this final rule to refer to Airbus Mandatory Service Bulletin A310–25–2205, Revision 01, dated November 19, 2010. We added a new paragraph (n) of this AD to provide credit for doing actions before the effective date of this AD in accordance with Airbus Mandatory Service Bulletin A310–25–2205, dated August 31, 2009, for Airbus Model A310 series airplanes. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data, and determined that air safety and the public interest require adopting the AD with the changes described previously. E:\FR\FM\22MRR1.SGM 22MRR1

Agencies

[Federal Register Volume 76, Number 55 (Tuesday, March 22, 2011)]
[Rules and Regulations]
[Pages 15802-15805]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-6212]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0212; Directorate Identifier 2010-SW-055-AD; 
Amendment 39-16632; AD 2011-06-07]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France (Eurocopter) Model 
EC130 B4 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
Eurocopter Model EC130 B4 helicopters. This action requires identifying 
and inspecting a certain emergency flotation gear unit ``1G'' (1G 
unit). This action also requires modification of certain affected 1G 
units. This amendment is prompted by an uncommanded in-flight 
deployment of the emergency flotation gear when it was not armed by the 
crew. The actions specified in this AD are intended to prevent an 
uncommanded in-flight deployment of the emergency flotation gear, 
unexpected deceleration and pitch down movement of the helicopter, and 
subsequent loss of control of the helicopter.

DATES: Effective April 6, 2011.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 6, 2011.
    Comments for inclusion in the Rules Docket must be received on or 
before May 23, 2011.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-

[[Page 15803]]

30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, 
SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays.
    You may get the service information identified in this AD from 
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 
75053-4005, telephone (800) 232-0323, fax (972) 641-3710, or at https://www.eurocopter.com.

Examining the Docket

    You may examine the docket that contains the AD, any comments, and 
other information 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 Docket Operations 
office (telephone (800) 647-5527) is located in Room W12-140 on the 
ground floor of the West Building at the street address stated in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: George Schwab, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Safety Management Group, 2601 
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5114, fax 
(817) 222-5961.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD No. 2010-0088-E, dated May 6, 2010, to correct an unsafe condition 
for the Model EC130 B4 helicopters. EASA advises that an uncontrolled 
in-flight deployment of the emergency flotation gear (not armed) on an 
EC130 B4 helicopter has been reported. The flight crew heard a 
detonation followed by heavy vibrations and noticed the emergency 
flotation gear floats were inflating. Investigations on the emergency 
flotation gear control system revealed that a wire was damaged inside 
the 1G unit. This wire was damaged, due to interference with the screw 
securing cable 1GR19E lug to the bus bar, causing a short circuit in 
the emergency flotation gear deployment activation circuit and the 
consequent deployment of the emergency flotation gear. EASA further 
states the possibility of interference of the 1G unit's internal wire 
harnesses with a fuselage metal structure member (stringer) has been 
identified, which could have the same consequences.

Related Service Information

    Eurocopter has issued Emergency Alert Service Bulletin No. 25A037, 
dated April 27, 2010, for the Model EC130 B4 helicopters, which 
specifies inspecting 1G units without an ``*'' displayed on the 1G unit 
panel after the part number (P/N) and taking various corrective actions 
at various times pending installation of a conforming 1G unit. EASA 
classified this EASB as mandatory and issued AD No. 2010-0088-E, dated 
May 6, 2010, to ensure the continued airworthiness of these 
helicopters.

FAA's Evaluation and Unsafe Condition Determination

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

Differences Between This AD and the EASA AD

    This AD does not require the actions to be completed at the 
compliance times of 3 months and 8 months, nor does it require the 
repetitive actions specified in the EASA AD. This AD requires the 
actions to be done within 15 hours time-in-service (TIS). Also, this AD 
refers to flight hours as hours TIS.

FAA's Determination and Requirements of This AD

    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, this AD is being issued 
to prevent an uncommanded in-flight deployment of the emergency 
flotation gear, unexpected deceleration and pitch down movement of the 
helicopter, and subsequent loss of control of the helicopter.
    This AD requires determining if the 1G unit has an asterisk after 
the P/N displayed on the 1G unit panel. If an asterisk follows the P/N, 
the AD requires inspecting for a rubber extrusion installed on the 
stringer. If no rubber extrusion is installed on the stringer, the AD 
requires removing the 1G unit, bonding a rubber extrusion on the 
stringer, reinstalling the 1G unit, and functionally testing the 
emergency flotation gear control system. If no asterisk follows the P/
N, the AD requires removing the 1G unit and inspecting the 1G unit for 
interference between the harness wires and the stringer and between 
internal parts. Also, the AD requires if no rubber extrusion is 
installed on the stringer, protecting the stringer by bonding a rubber 
extrusion on the stringer. The AD also requires inspecting for 
interference between the attachment screw and the wires of the nearby 
harness and for damage to the wires of the harness. The AD also 
requires modifying the 1G unit as necessary to protect the 1G unit from 
interference. Also, the AD requires identifying the modified 1G unit by 
marking an asterisk after the P/N. The AD also requires reinstalling 
and functionally testing the 1G unit. Installing a conforming 1G unit 
is terminating action for the requirements of this AD. Do the actions 
by following specified portions of the service bulletin described 
previously.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability of the helicopter. This AD requires, within 15 hours 
TIS, determining whether a conforming 1G unit is installed, and if not, 
modifying the 1G unit within 15 hours TIS. Fifteen hours TIS is a very 
short compliance time; therefore, this AD must be issued immediately.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Costs of Compliance

    We estimate that this AD will affect about 119 helicopters of U.S. 
registry. Determining whether an asterisk is present on the 1G unit 
panel will require a minimal amount of time. We estimate that it will 
take about 8 work-hours per helicopter to remove, modify, and replace a 
1G unit. The average labor rate is $85 per work-hour. Required parts 
will cost about $25 per helicopter. Based on these figures, we estimate 
the cost of this AD on U.S. operators is $8,460, assuming 12 
helicopters will require modification of the 1G unit per this AD.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES. Include ``Docket No. FAA-2011-0212;

[[Page 15804]]

Directorate Identifier 2010-SW-055-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this AD. We will 
consider all comments received by the closing date and may amend this 
AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this AD. Using the search function of the 
docket Web site, you can find and read the comments to any of our 
dockets, including the name of the individual who sent the comment. You 
may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78).

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national Government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD. See the AD docket to examine the economic evaluation.

Authority for This Rulemaking

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

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2011-06-07 Eurocopter France: Amendment 39-16632; Docket No. FAA-
2011-0212; Directorate Identifier 2010-SW-055-AD.

    Applicability: Model EC130 B4 helicopters with a flotation gear 
unit ``1G'' (1G unit), part number (P/N) 350A63256300, installed, 
certificated in any category.
    Compliance: Within 15 hours time-in-service, unless accomplished 
previously.
    To prevent an uncommanded in-flight deployment of the emergency 
flotation gear, unexpected deceleration and pitch down movement of 
the helicopter, and subsequent loss of control of the helicopter, do 
the following:
    (a) Determine whether the 1G unit has an asterisk (*) after the 
P/N displayed on the 1G unit panel as shown in Figure 4 of 
Eurocopter Emergency Alert Service Bulletin No. 25A037, dated April 
27, 2010 (EASB).
    (b) If there is an asterisk after the P/N displayed on the 1G 
unit panel, determine if there is a rubber extrusion installed on 
the stringer as shown in Figure 6 of the EASB.
    (1) If no rubber extrusion is installed on the stringer, remove 
the 1G unit by following the Accomplishment Instructions, paragraph 
2.B.2.a. of the EASB.
    (2) Bond a rubber extrusion onto the stringer using Bostik 1400 
or an equivalent adhesive. Bostik 1400 is ready for use; if using an 
equivalent adhesive, follow the manufacturer's directions for 
preparation and application.
    (i) Thoroughly clean the bonding surfaces of the stringer; 
remove all traces of grease.
    (ii) Apply a uniform adhesive film on the bonding surfaces.
    (A) For Bostik 1400, allow to dry until tack free (about 15 
minutes).
    (B) For equivalent adhesive, follow the manufacturer's 
procedures.
    (iii) After adhesive application, assemble the bonding faces and 
press firmly to eliminate air bubbles. Maintain the pressure 
throughout the hardening period as described for the adhesive being 
used. For Bostik 1400, the adhesive hardens in about 48 hours at 
room temperature.
    (3) Reinstall the 1G unit by following the Accomplishment 
Instructions, paragraph 2.B.2.b., of the EASB. Functionally test the 
emergency flotation gear control system.
    (c) If there is no asterisk displayed after the P/N on the 1G 
unit panel, remove the 1G unit by following the Accomplishment 
Instructions, paragraph 2.B.2.a., of the EASB.
    (1) Inspect the 1G unit for interference:
    (i) If you find interference between the harness wires and the 
stringer, install a sheath, P/N EN6049-006-08-5, on all the 
harnesses in the area of the interference, and secure the sheath 
with cable ties as depicted in Figure 5 of the EASB.
    (ii) If you find interference between the harness wires and the 
inside surface of the 1G unit or with any of the 1G unit's internal 
components, remove the installed cable ties, P/N E0043-1A0P, and 
spacer(s), P/N E0688-01, as required, to allow repositioning or 
routing of the harness to eliminate interference. Secure 
repositioned harnesses using new cable ties, P/N E0043-1A0P, and new 
spacers, P/N E0688-01.
    (iii) If you find interference between the harness and the 
helicopter structural stringer, install a sheath, P/N EN6049-006-08-
5, on all the harnesses located at the stringer as depicted in 
Figures 5 and 6 of the EASB. Secure the sheath with cable ties, P/N 
E0043-1A0P, so that no interference between the sheathed harness and 
the structural stringer exists.
    (iv) Bond a black rubber extrusion, P/N BT4, on the stringer as 
shown in Figure 6 by following the requirements of paragraph (b)(2) 
of this AD.
    (2) Inspect the attachment screw of cable 1GR19E for orientation 
and arrangement that matches the Post EASB detail, as shown in 
insert D of Figure 5 of the EASB, and determine if it is covered 
with heat shrink, P/N VG95343T05E004A, or equivalent. If orientation 
and arrangement of the attachment screw cable 1GR19E are not as 
shown in insert D of Figure 5 or the attachment screw is not covered 
with heat shrink, modify the attachment screw by following the 
Accomplishment Instructions, paragraph 2.B.5.b., of the EASB.

    Note 1. Figure 5 of the EASB does not show the heat shrink 
installed for clarity of screw head and lug detail.

    (3) Inspect for damage to a wire of the harness inside the 1G 
unit as depicted in Figure 7 of the EASB. Replace any damaged wire 
using the correct wire and contact information listed in the 
Appendix, paragraph 4, of the EASB.
    (4) Mark an asterisk ``*'' after P/N 350A63256300 on the 1G unit 
panel using indelible ink to indicate compliance with this AD.
    (5) Reinstall the 1G unit by following the Accomplishment 
Instructions, paragraph 2.B.2.b., of the EASB, and functionally test 
the emergency flotation gear control system.
    (d) Installing an airworthy 1G unit that has been modified and 
identified as required by

[[Page 15805]]

this AD is terminating action for the requirements of this AD.
    (e) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Safety Management Group, FAA, Attn: George 
Schwab, Aviation Safety Engineer, Rotorcraft Directorate, 2601 
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5114, 
fax (817) 222-5961, for information about previously approved 
alternative methods of compliance.
    (f) The Joint Aircraft System/Component (JASC) Code is 2497: 
Electrical Power System Wiring.
    (g) Remove and install the 1G unit, determine the correct wire 
and contact information, and do the inspections by following the 
specified portions of Eurocopter Emergency Alert Service Bulletin 
No. 25A037, dated April 27, 2010. The Director of the Federal 
Register approved this incorporation by reference in accordance with 
5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from 
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 
75053-4005, telephone (800) 232-0323, fax (972) 641-3710, or at 
https://www.eurocopter.com. Copies may be inspected at the FAA, 
Office of the Regional Counsel, Southwest Region, 2601 Meacham 
Blvd., Room 663, Fort Worth, Texas, 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.
    (h) This amendment becomes effective on April 6, 2011.

    Note 2: The subject of this AD is addressed in European Aviation 
Safety Agency No. 2010-0088-E, dated May 6, 2010.


    Issued in Fort Worth, Texas, March 7, 2011.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-6212 Filed 3-21-11; 8:45 am]
BILLING CODE 4910-13-P
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