Airworthiness Directives; Bombardier, Inc. Airplanes, 63147-63151 [2015-26217]

Download as PDF Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules (d) Comments Due Date We must receive comments by December 18, 2015. (e) Compliance Issued in Fort Worth, Texas, on October 1, 2015. Lance T. Gant, Manager, Rotorcraft Directorate, Aircraft Certification Service. You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. [FR Doc. 2015–26229 Filed 10–16–15; 8:45 am] (f) Required Actions DEPARTMENT OF TRANSPORTATION Before further flight: (1) Revise the airspeed operating limitation in the Limitations section of the Rotorcraft Flight Manual (RFM) by making pen and ink changes or by inserting a copy of this AD into the RFM stating: ‘‘The never-exceed speed (VNE) is limited to 150 knots indicated airspeed (KIAS)’’ and ‘‘The rate-of-descent (R/D) must not exceed 1,500 ft/min when the airspeed is beyond 140 KIAS.’’ (2) Install one or more self-adhesive placards, with 6 millimeter red letters on white background, on the cockpit instrument panel in full view of the pilot and co-pilot to read as follows: ‘‘VNE LIMITED TO 150 KIAS’’ and ‘‘R/D MUST NOT EXCEED 1,500 ft/min when airspeed is beyond 140 KIAS’’ Federal Aviation Administration (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, Texas 76177; telephone (817) 222–5110; email 9-asw-ftwamoc-requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (h) Additional Information (1) Eurocopter Emergency Alert Service Bulletin (EASB) No. 01.00.60, 01.00.16, and 01.28, Revision 1, dated December 2, 2008, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641– 3775. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, Texas 76177. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2008–0204R1, dated May 21, 2014. You may view the EASA AD on the Internet at https://www.regulations.gov in Docket No. FAA–2015–4112. (j) Subject Joint Aircraft Service Component (JASC) Code 5310: Horizontal Stabilizer Structure. VerDate Sep<11>2014 17:25 Oct 16, 2015 Jkt 238001 BILLING CODE 4910–13–P 14 CFR Part 39 [Docket No. FAA–2015–3986; Directorate Identifier 2015–NM–057–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC–8–400, –401, and –402 airplanes. This proposed AD was prompted by reports of chafing damage due to insufficient clearance on the main landing gear (MLG) stabilizer brace, the nacelle A-frame structure, and the adjacent electrical wiring harnesses. An insufficient fillet radius may also exist on certain airplanes. This proposed AD would require, depending on airplane configuration, an inspection of the nacelle A-frame structure for insufficient fillet radius; an inspection for cracking of affected structure, and rework or repair if necessary, and rework of the nacelle A-frame structure; repetitive inspections of the nacelle Aframe structure and the MLG stabilizer brace for insufficient clearance and damage, and repair if necessary, and rework of the nacelle A-frame structure, which would terminate the repetitive inspections; installation of new stop brackets and a shim on each MLG stabilizer brace assembly; and rework of the electrical wiring harnesses in the nacelle area. We are proposing this AD to detect and correct chafing damage and subsequent premature cracking and fracture of the nacelle A-frame structure, which could result in failure of the MLG stabilizer brace and loss of the MLG down-lock indication, which could adversely affect the safe landing of the airplane. DATES: We must receive comments on this proposed AD by December 3, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: SUMMARY: PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 63147 • 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 W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375– 4000; fax 416–375–4539; email thd.qseries@aero.bombardier.com; Internet https://www.bombardier.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 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 by searching for and locating Docket No. FAA–2015– 3986; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this 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: Aziz Ahmed, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE– 171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7329; fax 516–794–5531. 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–2015–3986; Directorate Identifier 2015–NM–057–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, E:\FR\FM\19OCP1.SGM 19OCP1 63148 Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules 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 Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2014–45, dated December 23, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition on certain Bombardier, Inc. Model DHC–8–400, –401, and –402 airplanes. The MCAI states: asabaliauskas on DSK5VPTVN1PROD with PROPOSALS The aeroplane manufacturer has discovered that an insufficient fillet radius may exist on the flange of the nacelle Aframe structure on certain aeroplanes. There have also been several in-service reports of chafing damage on the main landing gear (MLG) stabilizer brace, the nacelle A-frame structure and its adjacent electrical wiring harnesses due to insufficient clearance. An insufficient fillet radius and chafing damage on the nacelle A-frame structure and MLG stabilizer brace could lead to premature cracking. Fracture of the nacelle A-frame structure or failure of the MLG stabilizer brace could adversely affect the safe landing of the aeroplane. The damage to the electrical wiring harnesses could result in the loss of the MLG downlock indication. This [Canadian] AD mandates the inspection and rework of the nacelle A-frame structure, and the rework of the forward MLG stabilizer brace assembly and the electrical harnesses in the nacelle area adjacent to the A-frame structure. Required actions include, depending on airplane configuration, the following actions: • A detailed inspection of the nacelle A-frame structure for insufficient fillet radius, an eddy current or fluorescent dye penetrant inspection for cracking of affected structure, and rework or repair if necessary. • Rework of the left-hand (LH) side and right-hand (RH) side nacelle Aframe structure, including doing a measurement of the clearance between the fasteners/A-frame structure and MLG stabilizer brace assembly and making sure no fouling condition exists, and repair if necessary. • Repetitive detailed inspections of the nacelle A-frame structure and the MLG stabilizer brace for insufficient clearance and damage, and repair if necessary. VerDate Sep<11>2014 17:25 Oct 16, 2015 Jkt 238001 • Rework of the nacelle A-frame structure, including a measurement of the clearance between the A-frame structure and MLG stabilizer brace assembly and a fluorescent dye penetrant inspection or high frequency eddy current inspection for cracking and repair if necessary, which would terminate the repetitive inspections. • Installation of new stop brackets and a shim on each MLG stabilizer brace assembly. • Rework of the electrical wiring harnesses in the nacelle area. The rework includes a detailed inspection of the conduit assembly for certain conditions and repair if any condition is found, replacement of damaged conduit, a measurement of the clearance between the stabilizer brace and electrical harness on both LH and RH nacelles to make sure there is 0.100 inch (2.54 millimeters (mm)) minimum clearance between the MLG stabilizer brace, and a check for damage on the A-frame structure and MLG stabilizer brace and repair if necessary. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 3986. Related Service Information Under 1 CFR Part 51 Bombardier has issued the following service information. • ModSum IS4Q2400028, Revision B, dated June 22, 2012; and ModSum IS4Q240029, Revision A, dated July 6, 2014. These modsums describe procedures for rerouting certain electrical harnesses and installing grommets. • ModSum IS4Q5450002, Revision B, dated April 30, 2012. This modsum describes procedures for installing specified fasteners on the MLG A-frame, in both the LH and RH nacelles. • ModSum IS4Q5450003, Revision C, released November 29, 2012. This modsum describes procedures for trimming the horizontal and vertical stiffeners on the MLG A frame in both the LH and RH nacelles. • Service Bulletin 84–32–112, Revision B, dated September 12, 2014, and Goodrich Service Bulletin 46400– 32–102R1, Revision 1, dated June 24, 2013, as referenced in Bombardier Service Bulletin 84–32–112, Revision B, dated September 12, 2014. This service information describes procedures for incorporating Bombardier ModSum 4– 902416 by installing new stop brackets and new stop shims for all MLG stabilizer brace assemblies. • Service Bulletin 84–32–114, Revision A, dated September 18, 2013. PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 This service information describes procedures for rework of the electrical wiring harnesses in the nacelle area. The rework includes a detailed inspection of the conduit assembly for certain conditions and repair, replacement of damaged conduit, a measurement of the clearance to make sure there is 0.100 inch (2.54 mm) minimum clearance between the MLG stabilizer brace, and a check for damage on the A-frame structure and MLG stabilizer brace and repair. • Service Bulletin 84–54–19, dated April 18, 2013. This service information describes procedures for detailed inspections of the nacelle A-frame structure for insufficient fillet radius, an eddy current or fluorescent dye penetrant inspection for cracking of affected structure, and rework or repair. • Service Bulletin 84–54–20, Revision B, dated October 2, 2014. This service information describes procedures for detailed inspections of the nacelle Aframe structure and the MLG stabilizer brace for insufficient clearance and damage, and repair. This service information also describes procedures for rework of the nacelle A-frame structure, including a measurement of the clearance between the A-frame structure and MLG stabilizer brace assembly, and a fluorescent dye penetrant inspection or high frequency eddy current inspection for cracking and repair, which would end the inspections. • Service Bulletin 84–54–21, dated May 9, 2013. This service information describes procedures for rework of the LH side and RH side nacelle A-frame structure, including a measurement of the clearance between the fasteners/Aframe structure and MLG stabilizer brace assembly and to make sure no fouling condition exists, and repair. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this NPRM. 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 E:\FR\FM\19OCP1.SGM 19OCP1 Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules develop on other products of the same type design. under the criteria of the Regulatory Flexibility Act. Costs of Compliance We estimate that this proposed AD affects 80 airplanes of U.S. registry. We also estimate that it would take up to 50 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 $8,452 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be up to $1,016,160, or $12,702 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. 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 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. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS Authority for This Rulemaking ■ 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); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities VerDate Sep<11>2014 17:25 Oct 16, 2015 Jkt 238001 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): Bombardier, Inc.: Docket No. FAA–2015– 3986; Directorate Identifier 2015–NM–057– AD. (a) Comments Due Date We must receive comments by December 3, 2015. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc. Model DHC–8–400, –401, and –402 airplanes, certificated in any category, serial numbers (S/Ns) 4001 through 4431 inclusive. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Reason This AD was prompted by reports of chafing damage due to insufficient clearance on the main landing gear (MLG) stabilizer brace, the nacelle A-frame structure, and the adjacent electrical wiring harnesses. An insufficient fillet radius might also exist on certain airplanes. We are issuing this AD to detect and correct chafing damage and subsequent premature cracking and fracture of the nacelle A-frame structure, which could result in failure of the MLG stabilizer brace and loss of the MLG down-lock indication, which could adversely affect the safe landing of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection, Corrective Actions if Necessary, and Rework For airplanes having S/Ns 4001 through 4055 inclusive: Do the actions required by paragraphs (g)(1) and (g)(2) of this AD. (1) Within 600 flight hours or 100 days after the effective date of this AD, whichever PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 63149 occurs first: Do a detailed inspection of the left-hand (LH) side and right-hand (RH) side nacelle A-frame structure for insufficient fillet radius, in accordance with ‘‘Part A— Inspection’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–54–19, dated April 18, 2013. If an insufficient fillet radius exists, before further flight, do an eddy current or fluorescent dye penetrant inspection for cracking, in accordance with ‘‘Part A—Inspection’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–54–19, dated April 18, 2013. (i) If any cracking is found: Before further flight, repair using a method approved by the Manager, New York ACO, ANE–170, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). (ii) If no cracking is found: Before further flight, rework the structure, in accordance ‘‘Part B—Rectification’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–54–19, dated April 18, 2013. (2) Within 6,000 flight hours or 36 months after the effective date of this AD, whichever occurs first: Rework the LH side and RH side nacelle A-frame structure, including doing a measurement of the clearance between the fasteners/A-frame structure and MLG stabilizer brace assembly and making sure no fouling condition exists, in accordance with paragraph 3.B. ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–54–21, dated May 9, 2013. If the clearance is found to be less than 0.100 inch (2.54 millimeters (mm)) between the fasteners/A-frame structure and MLG stabilizer brace assembly after the rework is done, or a fouling condition exists during the extension of the MLG after rework is done, before further flight, repair using a method approved by the Manager, New York ACO, ANE–170, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. (h) Repetitive Inspections and Corrective Actions if Necessary For airplanes having S/Ns 4056 through 4426 inclusive: Within 600 flight hours or 100 days after the effective date of this AD, whichever occurs first: Do a detailed inspection of the LH side and RH side nacelle A-frame structure and upper surface of the MLG stabilizer brace for insufficient clearance and damage (e.g., cracking), in accordance with ‘‘Part A—Inspection,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–54–20, Revision B, dated October 2, 2014. If no damage is found and clearance is sufficient: Repeat the inspection thereafter at intervals not to exceed 600 flight hours until the terminating action required by paragraph (i) of this AD has been done. (1) If a clearance less than 0.100 inch (2.54 mm) exists between the A-frame structure and the MLG stabilizer brace assembly in the retracted position, after the rework is done, before further flight, repair using a method approved by the Manager, New York ACO, ANE–170, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. (2) If any damage is found: Before further flight, repair using a method approved by the E:\FR\FM\19OCP1.SGM 19OCP1 63150 Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules Manager, New York ACO, ANE–170, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. (i) Terminating Action for Certain Airplanes For airplanes having S/Ns 4056 through 4426 inclusive: Within 6,000 flight hours or 36 months after the effective date of this AD, whichever occurs first; Rework the LH side and RH side nacelle A-frame structure, including doing a measurement of the clearance between the A-frame structure and MLG stabilizer brace assembly and doing a fluorescent dye penetrant inspection or high frequency eddy current inspection for cracking, in accordance with ‘‘Part BRework,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–54–20, Revision B, dated October 2, 2014. Accomplishment of the actions required by this paragraph terminates the repetitive inspections required by paragraph (h) of this AD. (1) If a clearance less than 0.100 inch (2.54 mm) exists between the A-frame structure and the MLG stabilizer brace assembly in the retracted position after the rework is done, before further flight, repair using a method approved by the Manager, New York ACO, ANE–170, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. (2) If any cracking is found: Before further flight, repair using a method approved by the Manager, New York ACO, ANE–170, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (j) Modification of MLG Stabilizer Brace Assembly For airplanes having S/Ns 4001 through 4431 inclusive with a MLG stabilizer brace assembly having part number 46400–27 installed: Within 6,000 flight hours or 36 months after the effective date of this AD, whichever occurs first; incorporate Bombardier ModSum 4–902416 by installing new stop brackets and a new shim on each MLG stabilizer brace assembly, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–32–112, Revision B, dated September 12, 2014, and Goodrich Service Bulletin 46400–32–102R1, Revision 1, dated June 24, 2013, as referenced in Bombardier Service Bulletin 84–32–112, Revision B, dated September 12, 2014. (k) Rework of the Electrical Wiring Harnesses For airplanes having S/Ns 4001 through 4411 inclusive: Within 6,000 flight hours or 36 months after the effective date of this AD, whichever occurs first; rework the LH and RH sides of the electrical wiring harnesses in the nacelle area adjacent to the A-frame structure, including doing the actions specified in paragraphs (k)(1) through (k)(4) of this AD, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–32–114, Revision A, dated September 18, 2013. If any damage is found on the A-frame structure or MLG stabilizer brace, before further flight, repair using a method approved by the Manager, New York ACO, ANE–170, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. (1) Doing a detailed inspection of the conduit assembly for the conditions specified in Bombardier Service Bulletin 84–32–114, VerDate Sep<11>2014 17:25 Oct 16, 2015 Jkt 238001 Revision A, dated September 18, 2013, and, before further flight, repairing if any condition is found. (2) Replacing damaged conduit. (3) Measuring the clearance between the stabilizer brace and electrical harness on both LH and RH nacelles to make sure there is 0.100 inch (2.54 mm) minimum clearance between the MLG stabilizer brace. (4) Checking for damage on the A-frame structure and MLG stabilizer brace. (l) Optional Installations (1) Installing specified fasteners on the MLG A-frame, in both LH and RH nacelles, in accordance with Bombardier ModSum IS4Q5450002, Revision B, dated April 30, 2012, is acceptable for compliance with the actions specified in paragraph (g) of this AD, provided the actions specified in Bombardier ModSum IS4Q5450002 are done within the compliance time specified in paragraph (g) of this AD, except where ModSum IS4Q5450002, Revision B, dated April 30, 2012, specifies to contact Bombardier for reduced clearances, before further flight, repair using a method approved by the Manager, New York ACO, ANE–170, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. (2) Trimming the horizontal and vertical stiffeners on MLG A-frame in both LH and RH nacelles, in accordance with Bombardier ModSum IS4Q5450003, Revision C, released November 29, 2012, is acceptable for compliance with the actions specified in paragraph (i) of this AD, provided the actions specified in Bombardier ModSum IS4Q5450003 are done within the compliance time specified in paragraph (i) of this AD, except where ModSum IS4Q5450003, Revision C, released November 29, 2012, specifies to contact Bombardier for reduced clearances, before further flight, repair using a method approved by the Manager, New York ACO, ANE–170, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. (3) Rerouting certain electrical harnesses and installing grommets, in accordance with Bombardier ModSum IS4Q2400028, Revision B, dated June 22, 2012 (for S/Ns 4001 through 4098 inclusive) or Bombardier ModSum IS4Q2400029, Revision A, dated July 6, 2014 (for S/Ns 4090 through 4411 inclusive), is acceptable for compliance with the actions specified in paragraph (k) of this AD, provided the actions specified in the applicable modsum are done within the compliance time specified in paragraph (k) of this AD, except where Bombardier ModSum IS4Q2400028, Revision B, dated June 22, 2012; and Bombardier ModSum IS4Q2400029, Revision A, dated July 6, 2014; specify to contact Bombardier to report stabilizer brace or structural damaged findings, before further flight, repair using a method approved by the Manager, New York ACO, ANE–170, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. (m) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraph (m)(1)(i) or (m)(1)(ii) of this AD. This service PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 information is not incorporated by reference in this AD. (i) Bombardier Service Bulletin 84–54–20, dated April 25, 2013. (ii) Bombardier Service Bulletin 84–54–20, Revision A, dated April 9, 2014. (2) This paragraph provides credit for actions required by paragraph (j) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraph (m)(2)(i) or (m)(2)(ii) of this AD. This service information is not incorporated by reference in this AD. (i) Bombardier Service Bulletin 84–32–112, dated December 20, 2012. (ii) Bombardier Service Bulletin 84–32– 112, Revision A, dated April 16, 2014. (3) This paragraph provides credit for actions required by paragraph (k) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 84–32–114, dated June 6, 2013. This service information is not incorporated by reference in this AD. (n) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO, ANE–170, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE–170, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2014–45, dated December 23, 2014, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2015–3986. (2) For service information identified in this AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; email thd.qseries@aero.bombardier.com; Internet https://www.bombardier.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 E:\FR\FM\19OCP1.SGM 19OCP1 Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on October 5, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–26217 Filed 10–16–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–4213; Directorate Identifier 2015–CE–022–AD] RIN 2120–AA64 Airworthiness Directives; Piper Aircraft, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Model PA–46–500TP airplanes. This proposed AD was prompted by a report of the wing upper skin joints being manufactured without sealant, which allows water to enter and stay in sealed, bonded stringers. This proposed AD would require inspecting the upper wing surface for sealant; inspecting the wing stringers for water intrusion; inspecting for deformation and corrosion if evidence of water intrusion exists; and taking corrective actions as necessary. We are proposing this AD to correct the unsafe condition on these products. DATES: We must receive comments on this proposed AD by December 3, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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: Deliver to Mail address above between 9 a.m. and 5 asabaliauskas on DSK5VPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 17:25 Oct 16, 2015 Jkt 238001 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Piper Aircraft, Inc., Customer Service, 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (877) 879–0275; fax: none; email: customer.service@piper.com; Internet: www.piper.com. You may review the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 4213; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Gregory ‘‘Keith’’ Noles, Aerospace Engineer, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, Georgia 30337; phone: (404) 474–5551; fax: (404) 474– 5606; email: gregory.noles@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2015–4213; Directorate Identifier 2015– CE–022–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 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 PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 63151 substantive verbal contact we receive about this proposed AD. Discussion We received a report of wing upper skin joints on Piper Aircraft, Inc. Model PA–46–500TP airplanes being manufactured without sealant, which allows water to enter and stay in sealed, bonded stringers. This condition, if not corrected, could result in water entering the stringers common to the upper wing skin. Left uncorrected, corrosion could develop, and freeze/thaw cycles of water at this location could cause deformation of the skin with follow-on disbonding between the stringer flanges and the inner surface of the wing skin. Consequently, the corrosion or disbonding could reduce the structural integrity of the wing. Related Service Information Under 1 CFR Part 51 We reviewed Piper Aircraft, Inc. Service Bulletin No. 1262B, dated April 23, 2015. The service bulletin provides instructions for inspecting the upper wing surface for sealant and sealing or resealing (if necessary). This service bulletin also provides instructions for inspecting the wing stringers for water intrusion, and, if water intrusion was found as a result of the inspection, inspecting for corrosion or deformation. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this NPRM. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously. Costs of Compliance We estimate that this proposed AD affects 440 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: E:\FR\FM\19OCP1.SGM 19OCP1

Agencies

[Federal Register Volume 80, Number 201 (Monday, October 19, 2015)]
[Proposed Rules]
[Pages 63147-63151]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-26217]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3986; Directorate Identifier 2015-NM-057-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. 
This proposed AD was prompted by reports of chafing damage due to 
insufficient clearance on the main landing gear (MLG) stabilizer brace, 
the nacelle A-frame structure, and the adjacent electrical wiring 
harnesses. An insufficient fillet radius may also exist on certain 
airplanes. This proposed AD would require, depending on airplane 
configuration, an inspection of the nacelle A-frame structure for 
insufficient fillet radius; an inspection for cracking of affected 
structure, and rework or repair if necessary, and rework of the nacelle 
A-frame structure; repetitive inspections of the nacelle A-frame 
structure and the MLG stabilizer brace for insufficient clearance and 
damage, and repair if necessary, and rework of the nacelle A-frame 
structure, which would terminate the repetitive inspections; 
installation of new stop brackets and a shim on each MLG stabilizer 
brace assembly; and rework of the electrical wiring harnesses in the 
nacelle area. We are proposing this AD to detect and correct chafing 
damage and subsequent premature cracking and fracture of the nacelle A-
frame structure, which could result in failure of the MLG stabilizer 
brace and loss of the MLG down-lock indication, which could adversely 
affect the safe landing of the airplane.

DATES: We must receive comments on this proposed AD by December 3, 
2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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 W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, 
Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375-
4539; email thd.qseries@aero.bombardier.com; Internet https://www.bombardier.com. You may view this referenced service information at 
the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
WA. 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 by searching for and locating Docket No. FAA-2015-
3986; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this 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: Aziz Ahmed, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; telephone 516-228-7329; fax 516-794-5531.

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-2015-3986; 
Directorate Identifier 2015-NM-057-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory,

[[Page 63148]]

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

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2014-45, dated December 23, 2014 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition on certain Bombardier, Inc. Model DHC-8-
400, -401, and -402 airplanes. The MCAI states:

    The aeroplane manufacturer has discovered that an insufficient 
fillet radius may exist on the flange of the nacelle A-frame 
structure on certain aeroplanes. There have also been several in-
service reports of chafing damage on the main landing gear (MLG) 
stabilizer brace, the nacelle A-frame structure and its adjacent 
electrical wiring harnesses due to insufficient clearance.
    An insufficient fillet radius and chafing damage on the nacelle 
A-frame structure and MLG stabilizer brace could lead to premature 
cracking. Fracture of the nacelle A-frame structure or failure of 
the MLG stabilizer brace could adversely affect the safe landing of 
the aeroplane. The damage to the electrical wiring harnesses could 
result in the loss of the MLG downlock indication.
    This [Canadian] AD mandates the inspection and rework of the 
nacelle A-frame structure, and the rework of the forward MLG 
stabilizer brace assembly and the electrical harnesses in the 
nacelle area adjacent to the A-frame structure.

    Required actions include, depending on airplane configuration, the 
following actions:
     A detailed inspection of the nacelle A-frame structure for 
insufficient fillet radius, an eddy current or fluorescent dye 
penetrant inspection for cracking of affected structure, and rework or 
repair if necessary.
     Rework of the left-hand (LH) side and right-hand (RH) side 
nacelle A-frame structure, including doing a measurement of the 
clearance between the fasteners/A-frame structure and MLG stabilizer 
brace assembly and making sure no fouling condition exists, and repair 
if necessary.
     Repetitive detailed inspections of the nacelle A-frame 
structure and the MLG stabilizer brace for insufficient clearance and 
damage, and repair if necessary.
     Rework of the nacelle A-frame structure, including a 
measurement of the clearance between the A-frame structure and MLG 
stabilizer brace assembly and a fluorescent dye penetrant inspection or 
high frequency eddy current inspection for cracking and repair if 
necessary, which would terminate the repetitive inspections.
     Installation of new stop brackets and a shim on each MLG 
stabilizer brace assembly.
     Rework of the electrical wiring harnesses in the nacelle 
area. The rework includes a detailed inspection of the conduit assembly 
for certain conditions and repair if any condition is found, 
replacement of damaged conduit, a measurement of the clearance between 
the stabilizer brace and electrical harness on both LH and RH nacelles 
to make sure there is 0.100 inch (2.54 millimeters (mm)) minimum 
clearance between the MLG stabilizer brace, and a check for damage on 
the A-frame structure and MLG stabilizer brace and repair if necessary.

You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3986.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued the following service information.
     ModSum IS4Q2400028, Revision B, dated June 22, 2012; and 
ModSum IS4Q240029, Revision A, dated July 6, 2014. These modsums 
describe procedures for rerouting certain electrical harnesses and 
installing grommets.
     ModSum IS4Q5450002, Revision B, dated April 30, 2012. This 
modsum describes procedures for installing specified fasteners on the 
MLG A-frame, in both the LH and RH nacelles.
     ModSum IS4Q5450003, Revision C, released November 29, 
2012. This modsum describes procedures for trimming the horizontal and 
vertical stiffeners on the MLG A frame in both the LH and RH nacelles.
     Service Bulletin 84-32-112, Revision B, dated September 
12, 2014, and Goodrich Service Bulletin 46400-32-102R1, Revision 1, 
dated June 24, 2013, as referenced in Bombardier Service Bulletin 84-
32-112, Revision B, dated September 12, 2014. This service information 
describes procedures for incorporating Bombardier ModSum 4-902416 by 
installing new stop brackets and new stop shims for all MLG stabilizer 
brace assemblies.
     Service Bulletin 84-32-114, Revision A, dated September 
18, 2013. This service information describes procedures for rework of 
the electrical wiring harnesses in the nacelle area. The rework 
includes a detailed inspection of the conduit assembly for certain 
conditions and repair, replacement of damaged conduit, a measurement of 
the clearance to make sure there is 0.100 inch (2.54 mm) minimum 
clearance between the MLG stabilizer brace, and a check for damage on 
the A-frame structure and MLG stabilizer brace and repair.
     Service Bulletin 84-54-19, dated April 18, 2013. This 
service information describes procedures for detailed inspections of 
the nacelle A-frame structure for insufficient fillet radius, an eddy 
current or fluorescent dye penetrant inspection for cracking of 
affected structure, and rework or repair.
     Service Bulletin 84-54-20, Revision B, dated October 2, 
2014. This service information describes procedures for detailed 
inspections of the nacelle A-frame structure and the MLG stabilizer 
brace for insufficient clearance and damage, and repair. This service 
information also describes procedures for rework of the nacelle A-frame 
structure, including a measurement of the clearance between the A-frame 
structure and MLG stabilizer brace assembly, and a fluorescent dye 
penetrant inspection or high frequency eddy current inspection for 
cracking and repair, which would end the inspections.
     Service Bulletin 84-54-21, dated May 9, 2013. This service 
information describes procedures for rework of the LH side and RH side 
nacelle A-frame structure, including a measurement of the clearance 
between the fasteners/A-frame structure and MLG stabilizer brace 
assembly and to make sure no fouling condition exists, and repair.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section of this 
NPRM.

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

[[Page 63149]]

develop on other products of the same type design.

Costs of Compliance

    We estimate that this proposed AD affects 80 airplanes of U.S. 
registry.
    We also estimate that it would take up to 50 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 $8,452 per 
product. Based on these figures, we estimate the cost of this proposed 
AD on U.S. operators to be up to $1,016,160, or $12,702 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this 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);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

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

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

    Bombardier, Inc.: Docket No. FAA-2015-3986; Directorate 
Identifier 2015-NM-057-AD.

(a) Comments Due Date

    We must receive comments by December 3, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc. Model DHC-8-400, -401, and -
402 airplanes, certificated in any category, serial numbers (S/Ns) 
4001 through 4431 inclusive.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of chafing damage due to 
insufficient clearance on the main landing gear (MLG) stabilizer 
brace, the nacelle A-frame structure, and the adjacent electrical 
wiring harnesses. An insufficient fillet radius might also exist on 
certain airplanes. We are issuing this AD to detect and correct 
chafing damage and subsequent premature cracking and fracture of the 
nacelle A-frame structure, which could result in failure of the MLG 
stabilizer brace and loss of the MLG down-lock indication, which 
could adversely affect the safe landing of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspection, Corrective Actions if Necessary, and Rework

    For airplanes having S/Ns 4001 through 4055 inclusive: Do the 
actions required by paragraphs (g)(1) and (g)(2) of this AD.
    (1) Within 600 flight hours or 100 days after the effective date 
of this AD, whichever occurs first: Do a detailed inspection of the 
left-hand (LH) side and right-hand (RH) side nacelle A-frame 
structure for insufficient fillet radius, in accordance with ``Part 
A--Inspection'' of the Accomplishment Instructions of Bombardier 
Service Bulletin 84-54-19, dated April 18, 2013. If an insufficient 
fillet radius exists, before further flight, do an eddy current or 
fluorescent dye penetrant inspection for cracking, in accordance 
with ``Part A--Inspection'' of the Accomplishment Instructions of 
Bombardier Service Bulletin 84-54-19, dated April 18, 2013.
    (i) If any cracking is found: Before further flight, repair 
using a method approved by the Manager, New York ACO, ANE-170, FAA; 
or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.'s 
TCCA Design Approval Organization (DAO).
    (ii) If no cracking is found: Before further flight, rework the 
structure, in accordance ``Part B--Rectification'' of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-54-19, 
dated April 18, 2013.
    (2) Within 6,000 flight hours or 36 months after the effective 
date of this AD, whichever occurs first: Rework the LH side and RH 
side nacelle A-frame structure, including doing a measurement of the 
clearance between the fasteners/A-frame structure and MLG stabilizer 
brace assembly and making sure no fouling condition exists, in 
accordance with paragraph 3.B. ``Procedure,'' of the Accomplishment 
Instructions of Bombardier Service Bulletin 84-54-21, dated May 9, 
2013. If the clearance is found to be less than 0.100 inch (2.54 
millimeters (mm)) between the fasteners/A-frame structure and MLG 
stabilizer brace assembly after the rework is done, or a fouling 
condition exists during the extension of the MLG after rework is 
done, before further flight, repair using a method approved by the 
Manager, New York ACO, ANE-170, FAA; or TCCA; or Bombardier, Inc.'s 
TCCA DAO.

(h) Repetitive Inspections and Corrective Actions if Necessary

    For airplanes having S/Ns 4056 through 4426 inclusive: Within 
600 flight hours or 100 days after the effective date of this AD, 
whichever occurs first: Do a detailed inspection of the LH side and 
RH side nacelle A-frame structure and upper surface of the MLG 
stabilizer brace for insufficient clearance and damage (e.g., 
cracking), in accordance with ``Part A--Inspection,'' of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-54-20, 
Revision B, dated October 2, 2014. If no damage is found and 
clearance is sufficient: Repeat the inspection thereafter at 
intervals not to exceed 600 flight hours until the terminating 
action required by paragraph (i) of this AD has been done.
    (1) If a clearance less than 0.100 inch (2.54 mm) exists between 
the A-frame structure and the MLG stabilizer brace assembly in the 
retracted position, after the rework is done, before further flight, 
repair using a method approved by the Manager, New York ACO, ANE-
170, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO.
    (2) If any damage is found: Before further flight, repair using 
a method approved by the

[[Page 63150]]

Manager, New York ACO, ANE-170, FAA; or TCCA; or Bombardier, Inc.'s 
TCCA DAO.

(i) Terminating Action for Certain Airplanes

    For airplanes having S/Ns 4056 through 4426 inclusive: Within 
6,000 flight hours or 36 months after the effective date of this AD, 
whichever occurs first; Rework the LH side and RH side nacelle A-
frame structure, including doing a measurement of the clearance 
between the A-frame structure and MLG stabilizer brace assembly and 
doing a fluorescent dye penetrant inspection or high frequency eddy 
current inspection for cracking, in accordance with ``Part B-
Rework,'' of the Accomplishment Instructions of Bombardier Service 
Bulletin 84-54-20, Revision B, dated October 2, 2014. Accomplishment 
of the actions required by this paragraph terminates the repetitive 
inspections required by paragraph (h) of this AD.
    (1) If a clearance less than 0.100 inch (2.54 mm) exists between 
the A-frame structure and the MLG stabilizer brace assembly in the 
retracted position after the rework is done, before further flight, 
repair using a method approved by the Manager, New York ACO, ANE-
170, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO.
    (2) If any cracking is found: Before further flight, repair 
using a method approved by the Manager, New York ACO, ANE-170, FAA; 
or TCCA; or Bombardier, Inc.'s TCCA DAO.

(j) Modification of MLG Stabilizer Brace Assembly

    For airplanes having S/Ns 4001 through 4431 inclusive with a MLG 
stabilizer brace assembly having part number 46400-27 installed: 
Within 6,000 flight hours or 36 months after the effective date of 
this AD, whichever occurs first; incorporate Bombardier ModSum 4-
902416 by installing new stop brackets and a new shim on each MLG 
stabilizer brace assembly, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 84-32-112, Revision B, 
dated September 12, 2014, and Goodrich Service Bulletin 46400-32-
102R1, Revision 1, dated June 24, 2013, as referenced in Bombardier 
Service Bulletin 84-32-112, Revision B, dated September 12, 2014.

(k) Rework of the Electrical Wiring Harnesses

    For airplanes having S/Ns 4001 through 4411 inclusive: Within 
6,000 flight hours or 36 months after the effective date of this AD, 
whichever occurs first; rework the LH and RH sides of the electrical 
wiring harnesses in the nacelle area adjacent to the A-frame 
structure, including doing the actions specified in paragraphs 
(k)(1) through (k)(4) of this AD, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-32-
114, Revision A, dated September 18, 2013. If any damage is found on 
the A-frame structure or MLG stabilizer brace, before further 
flight, repair using a method approved by the Manager, New York ACO, 
ANE-170, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO.
    (1) Doing a detailed inspection of the conduit assembly for the 
conditions specified in Bombardier Service Bulletin 84-32-114, 
Revision A, dated September 18, 2013, and, before further flight, 
repairing if any condition is found.
    (2) Replacing damaged conduit.
    (3) Measuring the clearance between the stabilizer brace and 
electrical harness on both LH and RH nacelles to make sure there is 
0.100 inch (2.54 mm) minimum clearance between the MLG stabilizer 
brace.
    (4) Checking for damage on the A-frame structure and MLG 
stabilizer brace.

(l) Optional Installations

    (1) Installing specified fasteners on the MLG A-frame, in both 
LH and RH nacelles, in accordance with Bombardier ModSum 
IS4Q5450002, Revision B, dated April 30, 2012, is acceptable for 
compliance with the actions specified in paragraph (g) of this AD, 
provided the actions specified in Bombardier ModSum IS4Q5450002 are 
done within the compliance time specified in paragraph (g) of this 
AD, except where ModSum IS4Q5450002, Revision B, dated April 30, 
2012, specifies to contact Bombardier for reduced clearances, before 
further flight, repair using a method approved by the Manager, New 
York ACO, ANE-170, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO.
    (2) Trimming the horizontal and vertical stiffeners on MLG A-
frame in both LH and RH nacelles, in accordance with Bombardier 
ModSum IS4Q5450003, Revision C, released November 29, 2012, is 
acceptable for compliance with the actions specified in paragraph 
(i) of this AD, provided the actions specified in Bombardier ModSum 
IS4Q5450003 are done within the compliance time specified in 
paragraph (i) of this AD, except where ModSum IS4Q5450003, Revision 
C, released November 29, 2012, specifies to contact Bombardier for 
reduced clearances, before further flight, repair using a method 
approved by the Manager, New York ACO, ANE-170, FAA; or TCCA; or 
Bombardier, Inc.'s TCCA DAO.
    (3) Rerouting certain electrical harnesses and installing 
grommets, in accordance with Bombardier ModSum IS4Q2400028, Revision 
B, dated June 22, 2012 (for S/Ns 4001 through 4098 inclusive) or 
Bombardier ModSum IS4Q2400029, Revision A, dated July 6, 2014 (for 
S/Ns 4090 through 4411 inclusive), is acceptable for compliance with 
the actions specified in paragraph (k) of this AD, provided the 
actions specified in the applicable modsum are done within the 
compliance time specified in paragraph (k) of this AD, except where 
Bombardier ModSum IS4Q2400028, Revision B, dated June 22, 2012; and 
Bombardier ModSum IS4Q2400029, Revision A, dated July 6, 2014; 
specify to contact Bombardier to report stabilizer brace or 
structural damaged findings, before further flight, repair using a 
method approved by the Manager, New York ACO, ANE-170, FAA; or TCCA; 
or Bombardier, Inc.'s TCCA DAO.

(m) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (i) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service information 
specified in paragraph (m)(1)(i) or (m)(1)(ii) of this AD. This 
service information is not incorporated by reference in this AD.
    (i) Bombardier Service Bulletin 84-54-20, dated April 25, 2013.
    (ii) Bombardier Service Bulletin 84-54-20, Revision A, dated 
April 9, 2014.
    (2) This paragraph provides credit for actions required by 
paragraph (j) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service information 
specified in paragraph (m)(2)(i) or (m)(2)(ii) of this AD. This 
service information is not incorporated by reference in this AD.
    (i) Bombardier Service Bulletin 84-32-112, dated December 20, 
2012.
    (ii) Bombardier Service Bulletin 84-32-112, Revision A, dated 
April 16, 2014.
    (3) This paragraph provides credit for actions required by 
paragraph (k) of this AD, if those actions were performed before the 
effective date of this AD using Bombardier Service Bulletin 84-32-
114, dated June 6, 2013. This service information is not 
incorporated by reference in this AD.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York ACO, ANE-170, FAA, has the authority to approve AMOCs for this 
AD, if requested using the procedures found in 14 CFR 39.19. In 
accordance with 14 CFR 39.19, send your request to your principal 
inspector or local Flight Standards District Office, as appropriate. 
If sending information directly to the ACO, send it to ATTN: Program 
Manager, Continuing Operational Safety, FAA, New York ACO, 1600 
Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-
7300; fax 516-794-5531. Before using any approved AMOC, notify your 
appropriate principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office/
certificate holding district office. The AMOC approval letter must 
specifically reference this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, New York ACO, 
ANE-170, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO. If approved 
by the DAO, the approval must include the DAO-authorized signature.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2014-45, dated December 
23, 2014, for related information. This MCAI may be found in the AD 
docket on the Internet at https://www.regulations.gov by searching 
for and locating Docket No. FAA-2015-3986.
    (2) For service information identified in this AD, contact 
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt 
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; 
fax 416-375-4539; email thd.qseries@aero.bombardier.com; Internet 
https://www.bombardier.com. You may view this service information at 
the FAA, Transport Airplane Directorate, 1601

[[Page 63151]]

Lind Avenue SW., Renton, WA. For information on the availability of 
this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on October 5, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-26217 Filed 10-16-15; 8:45 am]
 BILLING CODE 4910-13-P
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