Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0100 Airplanes, 68668-68671 [2011-28756]

Download as PDF 68668 Federal Register / Vol. 76, No. 215 / Monday, November 7, 2011 / Proposed Rules deteriorate with age. We are issuing this AD to prevent ignition of the BMS 8–39 or AMS 3570 polyurethane foam insulation on the duct assemblies of the ECS due to a potential electrical arc, which could start a small fire and lead to a larger fire that may spread throughout the airplane through the ECS. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Air Distribution Duct Rework Within 72 months after the effective date of this AD, rework the applicable duct assemblies in the ECS specified in and in accordance with the Accomplishment Instructions and Appendix A of Boeing Service Bulletin 737–21A1132, Revision 3, dated February 16, 2011. Note 1: The service bulletin accomplishment instructions might refer to other procedures. When the words ‘‘refer to’’ are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used to comply with the AD. When the words ‘‘in accordance with’’ are included in the instruction, the procedure in the design approval holder document must be used to comply with the AD. Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; phone: (425) 917–6495; fax: (425) 917– 6590; email: Kimberly.Devoe@faa.gov. (2) 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; phone: (206) 544–5000, extension 1; fax: (206) 766– 5680; email: me.boecom@boeing.com; 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. Issued in Renton, Washington, on October 26, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. (h) Credit for Actions Accomplished in Accordance With Previous Service Information Reworking the applicable duct assemblies in the ECS in accordance with the Accomplishment Instructions and Appendix A of Boeing Service Bulletin 737–21A1132, Revision 2, dated June 13, 2007, before the effective date of this AD is acceptable for compliance with the corresponding actions required by paragraph (g) of this AD. srobinson on DSK4SPTVN1PROD with PROPOSALS (i) Parts Installation As of the effective date of this AD, no person may install an ECS duct assembly with BMS 8–39 or AMS 3570 polyurethane foam insulation on any airplane. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle 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. Information may be emailed to: 9-ANM&Seattle-ACO-Requests-faa.gov. (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. (k) Related Information (1) For more information about this AD, contact Kimberly A. DeVoe, Aerospace Engineer, Cabin Safety and Environmental VerDate Mar<15>2010 17:46 Nov 04, 2011 Jkt 226001 [FR Doc. 2011–28758 Filed 11–4–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–1169; Directorate Identifier 2010–NM–050–AD] RIN 2120–AA64 Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0100 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed 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: [T]here have been a number of occurrences with Messier-Dowty MLG [main landing gear] units where the main fitting failed, due to fatigue cracking in the area of the filler and bleeder holes, and occurrences where the sliding member failed, due to fatigue cracking at the area of chrome run-out/lower radius of the sliding tube portion of the sliding member. Investigation has revealed that the most probable cause of * * * cracks is high compressive stress during braking at higher deceleration levels outside the regular fatigue load spectrum. [T]he high compressive stress locally exceeds the elasticity limit of the PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 material, leaving a residual tensile stress at release of the heavy braking load. Subsequently, this local residual tensile stress results in a negative effect on the fatigue life of the component. This condition, if not detected and corrected, could lead to failure of the MLG, possibly resulting in loss of control of the aeroplane during the landing rollout. * * * * * * * * The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by December 22, 2011. You may send comments by any of the following methods: • 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–30, West Building Ground Floor, Room W12–40, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For Fokker service information identified in this proposed AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; telephone: +31 (0)252–627–350; fax: +31 (0)252–627–211; email: technicalservices.fokkerservices@stork. com; Internet: https://www. myfokkerfleet.com. For Messier-Dowty service information identified in this proposed AD, contact Messier Services Americas, Customer Support Center, 45360 Severn Way, Sterling, Virginia 20166–8910; telephone: (703) 450–8233; fax: (703) 404–1621; Internet: https://techpubs. services.messier-dowty.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. ADDRESSES: 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 proposed AD, the E:\FR\FM\07NOP1.SGM 07NOP1 Federal Register / Vol. 76, No. 215 / Monday, November 7, 2011 / Proposed Rules regulatory 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 FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone: (425) 227–1137; fax: (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2011–1169; Directorate Identifier 2010–NM–050–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on 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 we receive about this proposed AD. srobinson on DSK4SPTVN1PROD with PROPOSALS Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2009–0269R1, dated March 11, 2010 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Since introduction of the F28 Mark 0100 aeroplane into airline service, there have been a number of occurrences with MessierDowty MLG [main landing gear] units where the main fitting failed, due to fatigue cracking in the area of the filler and bleeder holes, and occurrences where the sliding member failed, due to fatigue cracking at the area of chrome run-out/lower radius of the sliding tube portion of the sliding member. Investigation has revealed that the most probable cause of both the main fitting and sliding member cracks is high compressive stress during braking at higher deceleration levels outside the regular fatigue load spectrum. Starting at deceleration stress levels somewhat below limit load, the high compressive stress locally exceeds the elasticity limit of the material, leaving a residual tensile stress at release of the heavy braking load. Subsequently, this local VerDate Mar<15>2010 17:46 Nov 04, 2011 Jkt 226001 residual tensile stress results in a negative effect on the fatigue life of the component. This condition, if not detected and corrected, could lead to failure of the MLG, possibly resulting in loss of control of the aeroplane during the landing rollout. To address this unsafe condition, the Civil Aviation Authority of the Netherlands (CAA– NL) issued AD NL–2005–012 (EASA approval 2005–6363) [which corresponds to FAA 2007–04–23, Amendment 39–14956 (72 FR 8615, February 27, 2007)] to require repetitive inspections of the sliding member (Fokker Services SBF100–32–144) and AD NL–2006–003 (EASA approval 2006–0041) to require repetitive inspections of the main fitting (Fokker Services SBF100–32–146). Messier-Dowty has now developed a modification, resulting in a strengthened sliding member and a strengthened main fitting, which is the terminating action for these repetitive inspections. For the reasons described above, this [EASA] AD requires the modification and reidentification of the affected MLG units, or replacement of the affected MLG units with modified units. This [EASA] AD has been revised to * * * state that modification of an aeroplane * * * also constitutes terminating action for the actions required by CAA–NL AD (BLA) 2002–115/2 dated October 8, 2004 [which partially corresponds to FAA AD 2008–20– 03, Amendment 39–15682 (73 FR 56452, September 29, 2008)]. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Fokker Services B.V. has issued: • Fokker Service Bulletin SBF100– 32–155, dated July 23, 2009; • Fokker Service Bulletin SBF100– 32–097, dated September 30, 1995; • Fokker Service Bulletin SBF100– 32–132, dated December 5, 2001; and • Fokker Service Bulletin SBF100– 32–156, Revision 1, dated June 29, 2009. Messier-Dowty has issued Service Bulletin F100–32–112, dated July 17, 2009. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 68669 Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the proposed AD. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 4 products of U.S. registry. We also estimate that it would take about 30 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $520,000 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these costs. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $2,090,200, or $522,550 per product. 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. E:\FR\FM\07NOP1.SGM 07NOP1 68670 Federal Register / Vol. 76, No. 215 / Monday, November 7, 2011 / Proposed Rules Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed 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 a regulatory evaluation of the estimated costs to comply with this proposed 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Fokker Services B.V.: Docket No. FAA– 2011–1169; Directorate Identifier 2010– NM–050–AD. srobinson on DSK4SPTVN1PROD with PROPOSALS Comments Due Date (a) We must receive comments by December 22, 2011. Affected ADs (b) This AD affects: AD 98–06–26, Amendment 39–10404 (63 FR 13502, March 20, 1998); AD 98–13–32, Amendment 39– 10623 (63 FR 34581, June 25, 1998); AD 2004–14–01, Amendment 39–13710 (69 FR 41391, July 9, 2004); AD 2007–04–23, Amendment 39–14956 (72 FR 8615, February 27, 2007); AD 2008–20–03, Amendment 39– 15682 (73 FR 56452, September 29, 2008); and AD 2010–21–12, Amendment 39–16472 (75 FR 63042, October 14, 2010). VerDate Mar<15>2010 17:46 Nov 04, 2011 Jkt 226001 Applicability (c) This AD applies to Fokker Services B.V. Model F.28 Mark 0100 airplanes, certificated in any category, all serial numbers, equipped with Messier-Dowty (formerly Dowty-Rotol, Dowty Aerospace Gloucester) main landing gear (MLG). Subject (d) Air Transport Association (ATA) of America Code 32: Landing Gear. Reason (e) The mandatory continuing airworthiness information (MCAI) states: [T]here have been a number of occurrences with Messier-Dowty MLG [main landing gear] units where the main fitting failed, due to fatigue cracking in the area of the filler and bleeder holes, and occurrences where the sliding member failed, due to fatigue cracking at the area of chrome run-out/lower radius of the sliding tube portion of the sliding member. Investigation has revealed that the most probable cause of * * * cracks is high compressive stress during braking at higher deceleration levels outside the regular fatigue load spectrum. [T]he high compressive stress locally exceeds the elasticity limit of the material, leaving a residual tensile stress at release of the heavy braking load. Subsequently, this local residual tensile stress results in a negative effect on the fatigue life of the component. This condition, if not detected and corrected, could lead to failure of the MLG, possibly resulting in loss of control of the aeroplane during the landing rollout. * * * * * * * * Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Actions (g) Within 48 months after the effective date of this AD, do an inspection of the MLG to determine whether Messier-Dowty (formerly Dowty-Rotol, Dowty Aerospace Gloucester) main landing gear (MLG) units having Part Number (P/N) 201072011, 201072012, 201072013, 201072014, 201072015, or 201072016 are installed on the airplane. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number of the MLG unit can be conclusively determined from that review. If any of those part numbers is found, do the requirements of paragraph (h) of this AD. (h) If, during the inspection required by paragraph (g) of this AD, any Messier-Dowty (formerly Dowty-Rotol, Dowty Aerospace Gloucester) main landing gear (MLG) units having Part Number (P/N) 201072011, 201072012, 201072013, 201072014, 201072015, or 201072016 are found, within 48 months after the effective date of this AD, do the actions specified in paragraph (h)(1) or (h)(2) of this AD. (1) Replace each MLG unit having P/N 201072011, 201072012, 201072013, 201072014, 201072015, or 201072016, with a PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 MLG unit having P/N 201072017, P/N 201072019, or P/N 201072021 (for LH), as applicable; or P/N 201072018, P/N 201072020 or P/N 201072022 (for RH), as applicable; in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–32–155, dated July 23, 2009, and do the actions required in paragraph (j) of this AD. (2) Modify and re-identify each affected MLG unit identified in paragraph (c) of this AD, in accordance with the Accomplishment Instructions of Messier-Dowty Service Bulletin F100–32–112, dated July 17, 2009, and do the actions required in paragraph (j) of this AD. Parts Installation (i) As of the effective date of this AD, no person may install on any airplane a MLG unit having P/N 201072011, P/N 201072012, P/N 201072013, P/N 201072014, P/N 201072015, or P/N 201072016. Removing Placard and Airplane Flight Manual Amendment (j) Before further flight after accomplishing the actions required by paragraph (h) of this AD, remove the airplane flight manual amendment and placard that were installed as required by AD 2008–20–03, Amendment 39–15682 (73 FR 56452, September 29, 2008). Prior or Concurrent Actions (k) Prior to or concurrently with the action (replacement or modification) as required by paragraph (h) of this AD, accomplish the following actions: (1) Install the torque link spacer with changed outer diameter, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–32–097, dated September 30, 1995. (2) Remove, if installed, the water spray deflectors, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–32–132, dated December 5, 2001. (3) Replace all P/N AE70690E, P/N AE70691E, P/N AE99111E, and P/N AE99119E brake quick-disconnect couplings with improved units in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin SBF100–32–156, Revision 1, dated June 29, 2009. Accomplishing the actions required by this paragraph terminates the requirements of AD 2010–21–12, Amendment 39–16472 (75 FR 63042, October 14, 2010) for that airplane only. ADs Affected by Accomplishment of Paragraph (h) of This AD (l) Accomplishing the actions required by paragraph (h) of this AD terminates the requirements of the following ADs for that airplane only: AD 98–06–26, Amendment 39–10404 (63 FR 13502, March 20, 1998); AD 98–13–32, Amendment 39–10623 (63 FR 34581, June 25, 1998); AD 2007–04–23, Amendment 39–14956 (72 FR 8615, February 27, 2007); and AD 2008–20–03, Amendment 39–15682 (73 FR 56452, September 29, 2008). E:\FR\FM\07NOP1.SGM 07NOP1 Federal Register / Vol. 76, No. 215 / Monday, November 7, 2011 / Proposed Rules Other AD Affected by Accomplishment of Paragraph (h) of This AD DEPARTMENT OF TRANSPORTATION (m) Accomplishing the actions required by paragraph (h) of this AD terminates the requirements of AD 2004–14–01, Amendment 39–13710 (69 FR 41391, July 9, 2004), for that airplane only. Federal Aviation Administration FAA AD Differences RIN 2120–AA64 Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Airworthiness Directives; Airbus Airplanes Other FAA AD Provisions AGENCY: (n) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone: (425) 227–1137; fax: (425) 227–1149. 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. Related Information srobinson on DSK4SPTVN1PROD with PROPOSALS (o) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2009–0269R1, dated March 11, 2010; Fokker Service Bulletins SBF100–32– 155, dated July 23, 2009, SBF100–32–097, dated September 30, 1995, SBF100–32–132, dated December 5, 2001, and SBF100–32– 156, Revision 1, dated June 29, 2009; and Messier-Dowty Service Bulletin F100–32– 112, dated July 17, 2009; for related information. Issued in Renton, Washington, on October 26, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–28756 Filed 11–4–11; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 17:46 Nov 04, 2011 Jkt 226001 14 CFR Part 39 [Docket No. FAA–2011–1170; Directorate Identifier 2010–NM–264–AD] Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). We propose to adopt a new airworthiness directive (AD) for all 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), and Model A310 series airplanes that would supersede an existing AD. This proposed 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: One operator experienced failures of four Fuel Level Sensor-Amplifier (FLSA) and Multi Tank Indicators (MTI) units. FLSA and MTI failures have been identified as having been caused by incorrect connector sleeves materials fitted to the MTI units. Degradation of the electrical insulation sleeves of the Low-level indication lamps on the MTI of the flight deck can cause a short circuit that might result in high voltage being conveyed to the high and low level sensors in the wing tanks. This condition, if not corrected, could cause the level sensor to heat above acceptable limits, possibly resulting in fuel tank explosion, and consequent loss of the aeroplane. * * * * * The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by December 22, 2011. ADDRESSES: You may send comments by any of the following methods: • 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, PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 68671 M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For Airbus service information identified in this proposed AD, contact Airbus SAS–EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email: account.airwortheas@airbus.com; Internet https:// www.airbus.com. For GE Aviation service information identified in this proposed AD, contact GE Aviation, Customer Support Center, 1 Neumann Way, Cincinnati, Ohio 45215; telephone (513) 552–3272; email cs.techpubs@ge.com; Internet https:// www.geaviation.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. 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 proposed AD, the regulatory 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 FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2011–1170; Directorate Identifier 2010–NM–264–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. E:\FR\FM\07NOP1.SGM 07NOP1

Agencies

[Federal Register Volume 76, Number 215 (Monday, November 7, 2011)]
[Proposed Rules]
[Pages 68668-68671]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-28756]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1169; Directorate Identifier 2010-NM-050-AD]
RIN 2120-AA64


Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 
0100 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed 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:

    [T]here have been a number of occurrences with Messier-Dowty MLG 
[main landing gear] units where the main fitting failed, due to 
fatigue cracking in the area of the filler and bleeder holes, and 
occurrences where the sliding member failed, due to fatigue cracking 
at the area of chrome run-out/lower radius of the sliding tube 
portion of the sliding member.
    Investigation has revealed that the most probable cause of * * * 
cracks is high compressive stress during braking at higher 
deceleration levels outside the regular fatigue load spectrum. [T]he 
high compressive stress locally exceeds the elasticity limit of the 
material, leaving a residual tensile stress at release of the heavy 
braking load. Subsequently, this local residual tensile stress 
results in a negative effect on the fatigue life of the component.
    This condition, if not detected and corrected, could lead to 
failure of the MLG, possibly resulting in loss of control of the 
aeroplane during the landing rollout. * * *

* * * * *
The proposed AD would require actions that are intended to address the 
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by December 22, 
2011.

ADDRESSES: You may send comments by any of the following methods:
     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-30, West Building Ground Floor, Room W12-40, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For Fokker service information identified in this proposed AD, 
contact Fokker Services B.V., Technical Services Dept., P.O. Box 231, 
2150 AE Nieuw-Vennep, the Netherlands; telephone: +31 (0)252-627-350; 
fax: +31 (0)252-627-211; email: 
technicalservices.fokkerservices@stork.com; Internet: https://www.myfokkerfleet.com.
    For Messier-Dowty service information identified in this proposed 
AD, contact Messier Services Americas, Customer Support Center, 45360 
Severn Way, Sterling, Virginia 20166-8910; telephone: (703) 450-8233; 
fax: (703) 404-1621; Internet: https://techpubs.services.messier-dowty.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.

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 proposed AD, the

[[Page 68669]]

regulatory 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 FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone: (425) 
227-1137; fax: (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-1169; 
Directorate Identifier 2010-NM-050-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on 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 we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2009-0269R1, dated March 11, 2010 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Since introduction of the F28 Mark 0100 aeroplane into airline 
service, there have been a number of occurrences with Messier-Dowty 
MLG [main landing gear] units where the main fitting failed, due to 
fatigue cracking in the area of the filler and bleeder holes, and 
occurrences where the sliding member failed, due to fatigue cracking 
at the area of chrome run-out/lower radius of the sliding tube 
portion of the sliding member.
    Investigation has revealed that the most probable cause of both 
the main fitting and sliding member cracks is high compressive 
stress during braking at higher deceleration levels outside the 
regular fatigue load spectrum. Starting at deceleration stress 
levels somewhat below limit load, the high compressive stress 
locally exceeds the elasticity limit of the material, leaving a 
residual tensile stress at release of the heavy braking load. 
Subsequently, this local residual tensile stress results in a 
negative effect on the fatigue life of the component.
    This condition, if not detected and corrected, could lead to 
failure of the MLG, possibly resulting in loss of control of the 
aeroplane during the landing rollout. To address this unsafe 
condition, the Civil Aviation Authority of the Netherlands (CAA-NL) 
issued AD NL-2005-012 (EASA approval 2005-6363) [which corresponds 
to FAA 2007-04-23, Amendment 39-14956 (72 FR 8615, February 27, 
2007)] to require repetitive inspections of the sliding member 
(Fokker Services SBF100-32-144) and AD NL-2006-003 (EASA approval 
2006-0041) to require repetitive inspections of the main fitting 
(Fokker Services SBF100-32-146). Messier-Dowty has now developed a 
modification, resulting in a strengthened sliding member and a 
strengthened main fitting, which is the terminating action for these 
repetitive inspections.
    For the reasons described above, this [EASA] AD requires the 
modification and reidentification of the affected MLG units, or 
replacement of the affected MLG units with modified units.
    This [EASA] AD has been revised to * * * state that modification 
of an aeroplane * * * also constitutes terminating action for the 
actions required by CAA-NL AD (BLA) 2002-115/2 dated October 8, 2004 
[which partially corresponds to FAA AD 2008-20-03, Amendment 39-
15682 (73 FR 56452, September 29, 2008)].

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Fokker Services B.V. has issued:
     Fokker Service Bulletin SBF100-32-155, dated July 23, 
2009;
     Fokker Service Bulletin SBF100-32-097, dated September 30, 
1995;
     Fokker Service Bulletin SBF100-32-132, dated December 5, 
2001; and
     Fokker Service Bulletin SBF100-32-156, Revision 1, dated 
June 29, 2009.
    Messier-Dowty has issued Service Bulletin F100-32-112, dated July 
17, 2009. The actions described in this service information are 
intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 4 products of U.S. registry. We also estimate that 
it would take about 30 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Required parts would cost about $520,000 per product. Where 
the service information lists required parts costs that are covered 
under warranty, we have assumed that there will be no charge for these 
costs. As we do not control warranty coverage for affected parties, 
some parties may incur costs higher than estimated here. Based on these 
figures, we estimate the cost of the proposed AD on U.S. operators to 
be $2,090,200, or $522,550 per product.

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.

[[Page 68670]]

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
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 a regulatory evaluation of the estimated costs to 
comply with this proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Fokker Services B.V.: Docket No. FAA-2011-1169; Directorate 
Identifier 2010-NM-050-AD.

Comments Due Date

    (a) We must receive comments by December 22, 2011.

Affected ADs

    (b) This AD affects: AD 98-06-26, Amendment 39-10404 (63 FR 
13502, March 20, 1998); AD 98-13-32, Amendment 39-10623 (63 FR 
34581, June 25, 1998); AD 2004-14-01, Amendment 39-13710 (69 FR 
41391, July 9, 2004); AD 2007-04-23, Amendment 39-14956 (72 FR 8615, 
February 27, 2007); AD 2008-20-03, Amendment 39-15682 (73 FR 56452, 
September 29, 2008); and AD 2010-21-12, Amendment 39-16472 (75 FR 
63042, October 14, 2010).

Applicability

    (c) This AD applies to Fokker Services B.V. Model F.28 Mark 0100 
airplanes, certificated in any category, all serial numbers, 
equipped with Messier-Dowty (formerly Dowty-Rotol, Dowty Aerospace 
Gloucester) main landing gear (MLG).

Subject

    (d) Air Transport Association (ATA) of America Code 32: Landing 
Gear.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    [T]here have been a number of occurrences with Messier-Dowty MLG 
[main landing gear] units where the main fitting failed, due to 
fatigue cracking in the area of the filler and bleeder holes, and 
occurrences where the sliding member failed, due to fatigue cracking 
at the area of chrome run-out/lower radius of the sliding tube 
portion of the sliding member.
    Investigation has revealed that the most probable cause of * * * 
cracks is high compressive stress during braking at higher 
deceleration levels outside the regular fatigue load spectrum. [T]he 
high compressive stress locally exceeds the elasticity limit of the 
material, leaving a residual tensile stress at release of the heavy 
braking load. Subsequently, this local residual tensile stress 
results in a negative effect on the fatigue life of the component.
    This condition, if not detected and corrected, could lead to 
failure of the MLG, possibly resulting in loss of control of the 
aeroplane during the landing rollout. * * *
* * * * *

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Actions

    (g) Within 48 months after the effective date of this AD, do an 
inspection of the MLG to determine whether Messier-Dowty (formerly 
Dowty-Rotol, Dowty Aerospace Gloucester) main landing gear (MLG) 
units having Part Number (P/N) 201072011, 201072012, 201072013, 
201072014, 201072015, or 201072016 are installed on the airplane. A 
review of airplane maintenance records is acceptable in lieu of this 
inspection if the part number of the MLG unit can be conclusively 
determined from that review. If any of those part numbers is found, 
do the requirements of paragraph (h) of this AD.
    (h) If, during the inspection required by paragraph (g) of this 
AD, any Messier-Dowty (formerly Dowty-Rotol, Dowty Aerospace 
Gloucester) main landing gear (MLG) units having Part Number (P/N) 
201072011, 201072012, 201072013, 201072014, 201072015, or 201072016 
are found, within 48 months after the effective date of this AD, do 
the actions specified in paragraph (h)(1) or (h)(2) of this AD.
    (1) Replace each MLG unit having P/N 201072011, 201072012, 
201072013, 201072014, 201072015, or 201072016, with a MLG unit 
having P/N 201072017, P/N 201072019, or P/N 201072021 (for LH), as 
applicable; or P/N 201072018, P/N 201072020 or P/N 201072022 (for 
RH), as applicable; in accordance with the Accomplishment 
Instructions of Fokker Service Bulletin SBF100-32-155, dated July 
23, 2009, and do the actions required in paragraph (j) of this AD.
    (2) Modify and re-identify each affected MLG unit identified in 
paragraph (c) of this AD, in accordance with the Accomplishment 
Instructions of Messier-Dowty Service Bulletin F100-32-112, dated 
July 17, 2009, and do the actions required in paragraph (j) of this 
AD.

Parts Installation

    (i) As of the effective date of this AD, no person may install 
on any airplane a MLG unit having P/N 201072011, P/N 201072012, P/N 
201072013, P/N 201072014, P/N 201072015, or P/N 201072016.

Removing Placard and Airplane Flight Manual Amendment

    (j) Before further flight after accomplishing the actions 
required by paragraph (h) of this AD, remove the airplane flight 
manual amendment and placard that were installed as required by AD 
2008-20-03, Amendment 39-15682 (73 FR 56452, September 29, 2008).

Prior or Concurrent Actions

    (k) Prior to or concurrently with the action (replacement or 
modification) as required by paragraph (h) of this AD, accomplish 
the following actions:
    (1) Install the torque link spacer with changed outer diameter, 
in accordance with the Accomplishment Instructions of Fokker Service 
Bulletin SBF100-32-097, dated September 30, 1995.
    (2) Remove, if installed, the water spray deflectors, in 
accordance with the Accomplishment Instructions of Fokker Service 
Bulletin SBF100-32-132, dated December 5, 2001.
    (3) Replace all P/N AE70690E, P/N AE70691E, P/N AE99111E, and P/
N AE99119E brake quick-disconnect couplings with improved units in 
accordance with Part 2 of the Accomplishment Instructions of Fokker 
Service Bulletin SBF100-32-156, Revision 1, dated June 29, 2009. 
Accomplishing the actions required by this paragraph terminates the 
requirements of AD 2010-21-12, Amendment 39-16472 (75 FR 63042, 
October 14, 2010) for that airplane only.

ADs Affected by Accomplishment of Paragraph (h) of This AD

    (l) Accomplishing the actions required by paragraph (h) of this 
AD terminates the requirements of the following ADs for that 
airplane only: AD 98-06-26, Amendment 39-10404 (63 FR 13502, March 
20, 1998); AD 98-13-32, Amendment 39-10623 (63 FR 34581, June 25, 
1998); AD 2007-04-23, Amendment 39-14956 (72 FR 8615, February 27, 
2007); and AD 2008-20-03, Amendment 39-15682 (73 FR 56452, September 
29, 2008).

[[Page 68671]]

Other AD Affected by Accomplishment of Paragraph (h) of This AD

    (m) Accomplishing the actions required by paragraph (h) of this 
AD terminates the requirements of AD 2004-14-01, Amendment 39-13710 
(69 FR 41391, July 9, 2004), for that airplane only.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (n) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. Send information to ATTN: Tom 
Rodriguez, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
Washington 98057-3356; telephone: (425) 227-1137; fax: (425) 227-
1149. 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.

Related Information

    (o) Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2009-0269R1, dated March 11, 2010; Fokker 
Service Bulletins SBF100-32-155, dated July 23, 2009, SBF100-32-097, 
dated September 30, 1995, SBF100-32-132, dated December 5, 2001, and 
SBF100-32-156, Revision 1, dated June 29, 2009; and Messier-Dowty 
Service Bulletin F100-32-112, dated July 17, 2009; for related 
information.

    Issued in Renton, Washington, on October 26, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-28756 Filed 11-4-11; 8:45 am]
BILLING CODE 4910-13-P
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