Airworthiness Directives; Bombardier, Inc., Airplanes, 33185-33189 [2019-14045]

Download as PDF Federal Register / Vol. 84, No. 134 / Friday, July 12, 2019 / Proposed Rules hours at the address of the Docket Clerk or at https://www.regulations.gov. If this proposed rule is finalized, this information collection will be merged with the forms currently approved under OMB No. 0581–0178 (Vegetable and Specialty Crops). A 30-day comment period is provided to allow interested persons to respond to all parts of this proposal. All written comments timely received will be considered before a final determination is made on this matter. A small business guide on complying with fruit, vegetable, and specialty crop marketing agreements and orders may be viewed at: https://www.ams.usda.gov/ rules-regulations/moa/small-businesses. Any questions about the compliance guide should be sent to Richard Lower at the previously mentioned address in the FOR FURTHER INFORMATION CONTACT section. (vi) Disposal of inedible almond material received with no transfer of the material between accepted users. (vii) The Board may deny or revoke accepted user status at any time if the applicant or accepted user fails to meet the terms and conditions of § 981.442, or if the applicant or accepted user fails to meet the terms and conditions set forth in the accepted user application (Form ABC 34). (viii) The eligibility of accepted users shall be reviewed annually by the Board. Handlers will not receive credit towards their disposition obligations pursuant to paragraph (a)(4) of this section for inedible lots where the difference between the weight of the lot reported by the inspection agency on Form ABC 8 and the weight of the lot reported on the public weighmaster weight certificate exceeds 2.0 percent. * * * * * List of Subjects in 7 CFR Part 981 Dated: July 8, 2019. Bruce Summers, Administrator, Agricultural Marketing Service. Almonds, Marketing agreements, Nuts, Reporting and recordkeeping requirements. For the reasons set forth in the preamble, 7 CFR part 981 is proposed to be amended as follows: Federal Aviation Administration 1. The authority citation for 7 CFR part 981 continues to read as follows: ■ 14 CFR Part 39 [Docket No. FAA–2019–0479; Product Identifier 2019–NM–020–AD] Authority: 7 U.S.C. 601–674. 2. Amend § 981.442 by revising paragraph (a)(7) to read as follows: ■ jbell on DSK3GLQ082PROD with PROPOSALS RIN 2120–AA64 Quality Control. (a) * * * (7) Accepted Users. An accepted user’s eligibility shall be subject to the following criteria: (i) Annual completion of an application with the Board for accepted user status; (ii) Annual submission of a business data sheet to the Board; (iii) Annual submission of an Accepted User Plan (Form ABC 30) to the Board by July 31 of each year; (iv) The accurate and prompt submission of Form ABC 8 Part B to the Board for each lot of almonds received. Each lot of inedible almonds received must be supported by a public weighmaster weight certificate issued at the request of the accepted user at the time of receipt of the lot. Weighmaster weight certificates must be submitted to the Board within 10 business days of issuance; (v) Disposal of inedible almond material within 6 months of receipt; and VerDate Sep<11>2014 16:41 Jul 11, 2019 Jkt 247001 BILLING CODE 3410–02–P DEPARTMENT OF TRANSPORTATION PART 981—ALMONDS GROWN IN CALIFORNIA § 981.442 [FR Doc. 2019–14797 Filed 7–11–19; 8:45 am] Airworthiness Directives; Bombardier, Inc., Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede Airworthiness Directive (AD) 2009–09–02, which applies to certain Bombardier, Inc., Model DHC–8–400 series airplanes. AD 2009–09–02 requires repetitive inspections for damage of certain main landing gear (MLG) forward stabilizer brace assemblies, repetitive inspections for cracking of both MLG forward stabilizer braces, liquid penetrant inspections for cracking, and corrective actions if necessary. Since the FAA issued AD 2009–09–02, the FAA has determined that the installation of an elbow restrictor is necessary to address the unsafe condition which would extend the repetitive inspection interval. This proposed AD would retain the existing SUMMARY: PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 33185 actions and also require installation of an elbow restrictor. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by August 26, 2019. 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 p.m., Monday through Friday, except Federal holidays. For Bombardier service information identified in this NPRM, 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. For Goodrich service information identified in this NPRM, contact Collins Aerospace, 1400 South Service Road West, Oakville, Ontario L6L 5Y7, Canada; telephone: 905–827–7777. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. 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–2019– 0479; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7330; fax 516–794–5531; email 9avs-nyaco-cos@faa.gov. SUPPLEMENTARY INFORMATION: E:\FR\FM\12JYP1.SGM 12JYP1 33186 Federal Register / Vol. 84, No. 134 / Friday, July 12, 2019 / Proposed Rules Comments Invited The FAA invites 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–2019–0479; Product Identifier 2019–NM–020–AD’’ at the beginning of your comments. The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. The FAA will consider all comments received by the closing date and may amend this proposed AD based on those comments. The FAA will post all comments, without change, to https:// www.regulations.gov, including any personal information you provide. The FAA will also post a report summarizing each substantive verbal contact the agency receives about this proposed AD. Discussion The FAA issued AD 2009–09–02, Amendment 39–15888 (74 FR 18121, April 21, 2009) (‘‘AD 2009–09–02’’), for certain Bombardier Model DHC–8–400 series airplanes. AD 2009–09–02 requires inspections for damage (including excessive wear, corrosion, foreign object damage, and cracking) of certain MLG forward stabilizer brace assemblies and applicable corrective actions; and repetitive inspections for cracking of both MLG forward stabilizer braces, applicable liquid penetrant inspections for cracking, and corrective actions if necessary. AD 2009–09–02 resulted from reports of failures of the aft hinge of the MLG forward stabilizer brace due to fatigue cracks. The FAA issued AD 2009–09–02 to address failure of the stabilizer brace, which could result in the collapse of the MLG. jbell on DSK3GLQ082PROD with PROPOSALS Actions Since AD 2009–09–02 Was Issued Since the FAA issued AD 2009–09– 02, the FAA has determined that the installation of an elbow restrictor is necessary to address the unsafe condition which would extend the repetitive inspection interval. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian AD CF–2009–11R2, dated May 31, 2018 (referred to after this as the Mandatory VerDate Sep<11>2014 16:41 Jul 11, 2019 Jkt 247001 Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Model DHC–8–400 series airplanes. The MCAI states: the retract port of the lock actuator with a new custom elbow fitting. Bombardier has also issued Q400 All Operator Message 338, dated February 23, 2009, which the Director of the Federal Register approved for incorporation by reference as of May 6, 2009 (74 FR 18121, April 21, 2009). Bombardier has issued Repair Drawing 8/4–32–099, Issue 4, dated September 4, 2018. This service information describes procedures for a nondestructive inspection for damage (including excessive wear, corrosion, foreign object damage, and cracking) of the MLG forward stabilizer brace assembly, P/N 46401–7. Goodrich has issued Service Concession Request 026–09, Revision H, dated August 29, 2018. This service information describes procedures for a nondestructive inspection for damage of the MLG forward stabilizer brace assembly, P/N 46401–7, and applicable corrective actions. 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. Several reports have been received on failures of the aft hinge of the main landing gear (MLG) forward stabilizer brace. Laboratory examinations have found that the fatigue cracks were initiated from the dowel pin hole at the aft hinge lug of the MLG forward stabilizer brace where the stop bracket is attached. Failure of the stabilizer brace could result in the collapse of the main landing gear. The initial issue of this [Canadian] AD mandated initial inspections, repetitive inspections and rectification, as required, of the MLG forward stabilizer brace. Revision 1 of this [Canadian] AD mandated installation of an Elbow Restrictor (P/N 46610–1) to the MLG Down-lock Actuators as terminating action to the repeat inspections in Part I. The repeat inspections in Part IV are required for all Forward Stabilizer Brace Assemblies (P/N 46401–7) after Installation of the Elbow Restrictor (P/N 46610–1). Revision 2 of this [Canadian] AD, in Part III, gives credit for the accomplishment of earlier revisions of Bombardier Service Bulletin SB 84–32–69 and clarifies, in Part IV, when the initial and repeat inspections are required following the installation of the elbow restrictor (P/N 46610–1) in Part III of this [Canadian] AD. FAA’s Determination Required actions include repetitive inspections for damage of certain MLG forward stabilizer brace assemblies, repetitive inspections for cracking of both MLG forward stabilizer braces, applicable liquid penetrant inspections for cracking, applicable corrective actions including repair or replacement if necessary, rework of the MLG forward stabilizer brace, and installation of an elbow restrictor. 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–2019–0479. This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with the State of Design Authority, the FAA has been notified of the unsafe condition described in the MCAI and service information referenced above. The FAA is proposing this AD because the FAA evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. Related Service Information Under 1 CFR Part 51 Proposed Requirements of This NPRM Bombardier has issued Service Bulletin 84–32–69, Revision C, dated January 20, 2011. This service information describes procedures for installing an elbow restrictor with part number (P/N) 46610–1. Bombardier has issued Service Bulletin 84–32–76, Revision B, dated August 1, 2018. This service information describes procedures for replacing the standard elbow fitting at PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 This proposed AD would retain all requirements of AD 2009–09–02. This proposed AD would also require accomplishing the actions specified in the service information described previously. Costs of Compliance The FAA estimates that this proposed AD affects 54 airplanes of U.S. registry. The FAA estimates the following costs to comply with this proposed AD: E:\FR\FM\12JYP1.SGM 12JYP1 Federal Register / Vol. 84, No. 134 / Friday, July 12, 2019 / Proposed Rules 33187 ESTIMATED COSTS FOR REQUIRED ACTIONS Action Labor cost Retained actions from AD 2009–09–02 ......... New proposed actions .................................... 8 work-hours × $85 per hour = $680 ............. 19 work-hours × $85 per hour = $1,615 ........ jbell on DSK3GLQ082PROD with PROPOSALS The FAA has received no definitive data that would enable the agency to provide cost estimates for the oncondition actions specified in this proposed AD. According to the manufacturer, some or all of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. The FAA does not control warranty coverage for affected individuals. As a result, the FAA has included all known costs in the cost estimate. 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. The FAA is 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. This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes and associated appliances to the Director of the System Oversight Division. Regulatory Findings The FAA 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 VerDate Sep<11>2014 16:41 Jul 11, 2019 Jkt 247001 Parts cost 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) Will not affect intrastate aviation in Alaska, 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. 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 removing Airworthiness Directive (AD) 2009–09–02, Amendment 39–15888 (74 FR 18121, April 21, 2009), and adding the following new AD: ■ Bombardier, Inc.: Docket No. FAA–2019– 0479; Product Identifier 2019–NM–020– AD. (a) Comments Due Date The FAA must receive comments by August 26, 2019. (b) Affected ADs This AD replaces AD 2009–09–02, Amendment 39–15888 (74 FR 18121, April 21, 2009) (‘‘AD 2009–09–02’’). (c) Applicability This AD applies to Bombardier, Inc., Model DHC–8–400, –401, and –402 airplanes, certificated in any category, serial numbers 4001, 4003, and subsequent, equipped with main landing gear (MLG) forward stabilizer brace part number (P/N) 46401–7. PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 $0 10,867 Cost per product Cost on U.S. operators $680 12,482 $36,720 674,028 (d) Subject Air Transport Association (ATA) of America Code 32, Main landing gear. (e) Reason This AD was prompted by reports of failures of the aft hinge of the MLG forward stabilizer brace due to fatigue cracks. The FAA is issuing this AD to address failure of the stabilizer brace, which could result in the collapse of the MLG. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection and Corrective Actions, With Revised Service Information and Removed Reporting Requirement This paragraph restates the requirements of paragraph (f) of AD 2009–09–02, with new service information and removed reporting requirement. Unless already done, do the following actions: (1) At the applicable time specified in paragraph (g)(1)(i), (g)(1)(ii), (g)(1)(iii), or (g)(1)(iv) of this AD: Perform non-destructive inspections for damage of the MLG forward stabilizer brace assemblies P/N 46401–7, in accordance with Bombardier Repair Drawing 8/4–32–099, Issue 1, dated March 10, 2009, and Goodrich Service Concession Request 026–09, Revision B, dated March 10, 2009; or Bombardier Repair Drawing 8/4–32–099, Issue 4, dated September 4, 2018, and Goodrich Service Concession Request 026– 09, Revision H, dated August 29, 2018. Repeat the inspection thereafter at intervals not to exceed 2,000 flight cycles. As of the effective date of this AD, use Bombardier Repair Drawing 8/4–32–099, Issue 4, dated September 4, 2018, and Goodrich Service Concession Request 026–09, Revision H, dated August 29, 2018, for the actions required by this paragraph. (i) For airplanes with MLG forward stabilizer braces that have accumulated 12,000 or more total flight cycles as of May 6, 2009 (the effective date of AD 2009–09– 02): Inspect within 50 flight cycles after May 6, 2009. (ii) For airplanes with MLG forward stabilizer braces that have accumulated 9,000 or more total flight cycles but fewer than 12,000 total flight cycles as of May 6, 2009 (the effective date of AD 2009–09–02): Inspect before the accumulation of 12,050 total flight cycles, or within 500 flight cycles after May 6, 2009, whichever occurs earlier. (iii) For airplanes with MLG forward stabilizer braces that have accumulated 4,500 or more total flight cycles but fewer than 9,000 total flight cycles as of May 6, 2009 (the effective date of AD 2009–09–02): Inspect before the accumulation of 9,500 total flight E:\FR\FM\12JYP1.SGM 12JYP1 jbell on DSK3GLQ082PROD with PROPOSALS 33188 Federal Register / Vol. 84, No. 134 / Friday, July 12, 2019 / Proposed Rules cycles, or within 1,500 flight cycles after May 6, 2009, whichever occurs earlier. (iv) For airplanes with MLG forward stabilizer braces that have accumulated fewer than 4,500 total flight cycles as of May 6, 2009 (the effective date of AD 2009–09–02): Inspect before the accumulation of 6,000 total flight cycles. (2) If any damage is found during any inspection required by paragraph (g)(1) of this AD, before further flight, do all applicable corrective actions in accordance with Goodrich Service Concession Request 026–09, Revision B, dated March 10, 2009; or Goodrich Service Concession Request 026– 09, Revision H, dated August 29, 2018; except as provided by paragraphs (g)(3), (g)(4), (g)(5), and (g)(6) of this AD. As of the effective date of this AD, use Goodrich Service Concession Request 026–09, Revision H, dated August 29, 2018, for the actions required by this paragraph. (3) For airplanes on which step 24. of Goodrich Service Concession Request 026– 09, Revision B, dated March 10, 2009, has been done: Within 1,200 flight cycles after May 6, 2009 (the effective date of AD 2009– 09–02), rework the MLG forward stabilizer brace, and except for airplanes on which the rework has been done, within 600 flight cycles after May 6, 2009, do a detailed visual inspection for damage of the stabilizer brace apex lugs, in accordance with Goodrich Service Concession Request 026–09, Revision B, dated March 10, 2009; or Goodrich Service Concession Request 026–09, Revision H, dated August 29, 2018. If any damage is found, repair before further flight in accordance with Section C of Goodrich Service Concession Request 026–09, Revision B, dated March 10, 2009; or Section C of Goodrich Service Concession Request 026– 09, Revision H, dated August 29, 2018. As of the effective date of this AD, use Goodrich Service Concession Request 026–09, Revision H, dated August 29, 2018, for the actions required by this paragraph. (4) At the applicable time specified in paragraph (g)(4)(i), (g)(4)(ii), or (g)(4)(iii) of this AD, replace the forward stabilizer brace assembly, in accordance with Goodrich Service Concession Request 026–09, Revision B, dated March 10, 2009; or Goodrich Service Concession Request 026–09, Revision H, dated August 29, 2018. As of the effective date of this AD, use Goodrich Service Concession Request 026–09, Revision H, dated August 29, 2018, for the actions required by this paragraph. (i) For airplanes on which cracking is found during any inspection required by this AD, and the cracking exceeds the limit specified in paragraph (g)(4)(i)(A) or (g)(4)(i)(B) of this AD, as applicable: Replace the assembly before further flight. (A) For cracking found before the effective date of this AD: The limit specified in Section C of Goodrich Service Concession Request 026–09, Revision B, dated March 10, 2009. (B) For cracking found on or after the effective date of this AD: The limit specified in Section C or Section D of Goodrich Service Concession Request 026–09, Revision H, dated August 29, 2018. (ii) For airplanes on which any cracking is found after the rework specified in Section C VerDate Sep<11>2014 16:41 Jul 11, 2019 Jkt 247001 of Goodrich Service Concession Request 026– 09, Revision B, dated March 10, 2009; or specified in Section C or Section D of Goodrich Service Concession Request 026– 09, Revision H, dated August 29, 2018: Replace the assembly before further flight. (iii) For airplanes on which no cracking is found after the rework specified in Section C of Goodrich Service Concession Request 026– 09, Revision B, dated March 10, 2009; or specified in Section C or Section D of Goodrich Service Concession Request 026– 09, Revision H, dated August 29, 2018: Replace the assembly within 2,700 flight cycles after doing the rework. (5) If foreign object damage is found during any inspection required by this AD, or if damage is found to a forward stabilizer brace lug or stop bracket retention hole apex bushing, before further flight, repair using a method approved by the Manager, New York ACO Branch, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (6) If any crack is found during the visual inspection under 10X magnification, repair before further flight, in accordance with Goodrich Service Concession Request 026– 09, Revision B, dated March 10, 2009; or Goodrich Service Concession Request 026– 09, Revision H, dated August 29, 2018. As of the effective date of this AD, use Goodrich Service Concession Request 026–09, Revision H, dated August 29, 2018, for the actions required by this paragraph. (7) Before the accumulation of 6,000 total flight cycles on the MLG forward stabilizer braces, or within 600 flight hours after May 6, 2009 (the effective date of AD 2009–09– 02), whichever occurs later: Do a detailed visual inspection for cracking of both MLG forward stabilizer braces and do all applicable liquid penetrant inspections for cracking, in accordance with Bombardier Q400 All Operator Message 338, dated February 23, 2009. Repeat the inspection thereafter at intervals not to exceed 600 flight hours. If any cracking is found during any inspection required by this paragraph, repair before further flight in accordance with Bombardier Repair Drawing 8/4–32–099, Issue 1, dated March 10, 2009, and Goodrich Service Concession Request 026–09, Revision B, dated March 10, 2009; or Bombardier Repair Drawing 8/4–32–099, Issue 4, dated September 4, 2018, and Goodrich Service Concession Request 026–09, Revision H, dated August 29, 2018. As of the effective date of this AD, use Bombardier Repair Drawing 8/4–32–099, Issue 4, dated September 4, 2018, and Goodrich Service Concession Request 026–09, Revision H, dated August 29, 2018, to repair cracking found during any inspection required by this paragraph. (h) New Requirement of This AD: Installation of Elbow Restrictor Within 2,000 flight hours or 12 months, whichever occurs first, from the effective date of this AD: Install an elbow restrictor, P/N 46610–1, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–32–69, Revision C, dated January 20, 2011. PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 (i) Terminating Actions (1) Installation of an elbow restrictor as required by paragraph (h) of this AD terminates the repetitive inspection requirements of paragraphs (g)(1) and (g)(7) of this AD. (2) Installation of an elbow restrictor as required by paragraph (h) of this AD terminates the replacement of the forward stabilizer brace assembly requirement of paragraph (g)(4)(iii) of this AD. (j) New Requirement of This AD: Revised Repetitive Inspections of the MLG Forward Stabilizer Brace (1) Within 2,000 flight cycles after the installation specified in paragraph (h) of this AD, or within 12 months after the effective date, whichever occurs later, do the nondestructive inspection, in accordance with Bombardier Repair Drawing 8/4–32–099, Issue 4, dated September 4, 2018, and Goodrich Service Concession Request 026– 09, Revision H, dated August 29, 2018. Thereafter, repeat the non-destructive inspection at the times specified in paragraph (j)(2) of this AD. (2) Repeat the non-destructive inspection required in paragraph (j)(1) of this AD at the applicable intervals specified in paragraphs (j)(2)(i), (j)(2)(ii), and (j)(2)(iii) of this AD. (i) For forward stabilizer braces, P/N 46401–7, that have not had any required rework done, as specified in Goodrich Service Concession Request 026–09, Section C or D, and have had Bombardier Service Bulletin 84–32–69 or Bombardier Service Bulletin 84–32–76 incorporated: Do the nondestructive inspection at intervals not to exceed 6,000 flight cycles. (ii) For forward stabilizer braces, P/N 46401–7, that have been reworked in accordance with Goodrich Service Concession Request 026–09, Section D, and have had Bombardier Service Bulletin 84– 32–69 or Bombardier Service Bulletin 84–32– 76 incorporated: Do the non-destructive inspection at intervals not to exceed 6,000 flight cycles. (iii) For forward stabilizer braces, P/N 46401–7, that have been reworked in accordance with Goodrich Service Concession Request 026–09, Section C, and have had Bombardier Service Bulletin 84– 32–69 or Bombardier Service Bulletin 84–32– 76 incorporated: Do the non-destructive inspection at intervals not to exceed 3,000 flight cycles. (k) Acceptable Method of Compliance for Paragraph (h) of This AD Replacing the standard elbow fitting at the retract port of the lock actuator with a new custom elbow fitting in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–32–76, Revision B, dated August 1, 2018, is an acceptable method of compliance for the installation required by paragraph (h) of this AD. (l) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using the service information in paragraph (l)(1)(i), (l)(1)(ii), or (l)(1)(iii) of this AD. E:\FR\FM\12JYP1.SGM 12JYP1 Federal Register / Vol. 84, No. 134 / Friday, July 12, 2019 / Proposed Rules (i) Bombardier Service Bulletin 84–32–69, dated June 30, 2009. (ii) Bombardier Service Bulletin 84–32–69, Revision A, dated August 19, 2009. (iii) Bombardier Service Bulletin 84–32–69, Revision B, dated September 17, 2009. (2) This paragraph provides credit for actions specified in paragraph (j) of this AD, if those actions were performed before the effective date of this AD using the service information in paragraph (l)(2)(i), (l)(2)(ii), or (l)(2)(iii) of this AD. (i) Bombardier Repair Drawing 8/4–32– 099, Issue 1, dated March 10, 2009, and Goodrich Service Concession Request 026– 09, Revision B, dated March 10, 2009. (ii) Bombardier Repair Drawing 8/4–32– 099, Issue 2, dated April 20, 2009, and Goodrich Service Concession Request 026– 09, Revision C, dated April 17, 2009. (iii) Bombardier Repair Drawing 8/4–32– 099, Issue 3, dated December 3, 2009, and Goodrich Service Concession Request 026– 09, Revision D, dated November 27, 2009. (3) This paragraph provides credit for actions performed using the method of compliance specified in paragraph (k) of this AD, if those actions were performed before the effective date of this AD using the service information in paragraph (l)(3)(i) or (l)(3)(ii) of this AD. (i) Bombardier Service Bulletin 84–32–76, dated May 20, 2010. (ii) Bombardier Service Bulletin 84–32–76, Revision A, dated June 19, 2014. jbell on DSK3GLQ082PROD with PROPOSALS (m) Other FAA AD Provisions (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO Branch, 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 certification office, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO Branch. AMOCs approved previously in accordance with AD 2009–09– 02 are approved as AMOCs for the corresponding requirements in paragraph (g) of 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 Branch, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian AD CF–2009–11R2, dated May 31, 2018, 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–2019–0479. (2) For more information about this AD, contact Andrea Jimenez, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; VerDate Sep<11>2014 16:41 Jul 11, 2019 Jkt 247001 telephone 516–228–7330; fax 516–794–5531; email 9-avs-nyaco-cos@faa.gov. (3) 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. For Goodrich service information identified in this NPRM, contact Collins Aerospace, 1400 South Service Road West, Oakville, Ontario L6L 5Y7, Canada; telephone: 905–827–7777. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Issued in Des Moines, Washington, on June 26, 2019. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–14045 Filed 7–11–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0524; Product Identifier 2019–NM–081–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747–400 and 747–400F series airplanes. This proposed AD was prompted by an evaluation that determined fatigue cracks could develop in the underwing longerons. This proposed AD would require repetitive inspections of the underwing longerons and certain fuselage skins for any crack, and applicable on-condition actions. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by August 26, 2019. SUMMARY: 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. ADDRESSES: PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 33189 • 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 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; internet https://www.myboeing fleet.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2019– 0524. 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–2019– 0524; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Eric Lin, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3523; email: eric.lin@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites 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–2019–0524; Product Identifier 2019–NM–081–AD’’ at the beginning of your comments. The FAA specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. The FAA will consider all comments received by the closing date and may amend this NPRM because of those comments. The FAA will post all comments received, without change, to https:// E:\FR\FM\12JYP1.SGM 12JYP1

Agencies

[Federal Register Volume 84, Number 134 (Friday, July 12, 2019)]
[Proposed Rules]
[Pages 33185-33189]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-14045]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0479; Product Identifier 2019-NM-020-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc., Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2009-09-02, which applies to certain Bombardier, Inc., Model DHC-8-400 
series airplanes. AD 2009-09-02 requires repetitive inspections for 
damage of certain main landing gear (MLG) forward stabilizer brace 
assemblies, repetitive inspections for cracking of both MLG forward 
stabilizer braces, liquid penetrant inspections for cracking, and 
corrective actions if necessary. Since the FAA issued AD 2009-09-02, 
the FAA has determined that the installation of an elbow restrictor is 
necessary to address the unsafe condition which would extend the 
repetitive inspection interval. This proposed AD would retain the 
existing actions and also require installation of an elbow restrictor. 
The FAA is proposing this AD to address the unsafe condition on these 
products.

DATES: The FAA must receive comments on this proposed AD by August 26, 
2019.

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 p.m., Monday through Friday, except Federal holidays.
    For Bombardier service information identified in this NPRM, 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 [email protected]; internet https://www.bombardier.com. For Goodrich service information identified in this 
NPRM, contact Collins Aerospace, 1400 South Service Road West, 
Oakville, Ontario L6L 5Y7, Canada; telephone: 905-827-7777. You may 
view this referenced service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For information 
on the availability of this material at the FAA, call 206-231-3195.

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-2019-
0479; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations is listed above. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer, 
Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 
Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7330; 
fax 516-794-5531; email [email protected].

SUPPLEMENTARY INFORMATION: 

[[Page 33186]]

Comments Invited

    The FAA invites 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-2019-0479; 
Product Identifier 2019-NM-020-AD'' at the beginning of your comments. 
The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. The 
FAA will consider all comments received by the closing date and may 
amend this proposed AD based on those comments.
    The FAA will post all comments, without change, to https://www.regulations.gov, including any personal information you provide. 
The FAA will also post a report summarizing each substantive verbal 
contact the agency receives about this proposed AD.

Discussion

    The FAA issued AD 2009-09-02, Amendment 39-15888 (74 FR 18121, 
April 21, 2009) (``AD 2009-09-02''), for certain Bombardier Model DHC-
8-400 series airplanes. AD 2009-09-02 requires inspections for damage 
(including excessive wear, corrosion, foreign object damage, and 
cracking) of certain MLG forward stabilizer brace assemblies and 
applicable corrective actions; and repetitive inspections for cracking 
of both MLG forward stabilizer braces, applicable liquid penetrant 
inspections for cracking, and corrective actions if necessary. AD 2009-
09-02 resulted from reports of failures of the aft hinge of the MLG 
forward stabilizer brace due to fatigue cracks. The FAA issued AD 2009-
09-02 to address failure of the stabilizer brace, which could result in 
the collapse of the MLG.

Actions Since AD 2009-09-02 Was Issued

    Since the FAA issued AD 2009-09-02, the FAA has determined that the 
installation of an elbow restrictor is necessary to address the unsafe 
condition which would extend the repetitive inspection interval.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD CF-2009-11R2, dated May 
31, 2018 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for certain Model DHC-8-400 series airplanes. The MCAI 
states:

    Several reports have been received on failures of the aft hinge 
of the main landing gear (MLG) forward stabilizer brace. Laboratory 
examinations have found that the fatigue cracks were initiated from 
the dowel pin hole at the aft hinge lug of the MLG forward 
stabilizer brace where the stop bracket is attached. Failure of the 
stabilizer brace could result in the collapse of the main landing 
gear.
    The initial issue of this [Canadian] AD mandated initial 
inspections, repetitive inspections and rectification, as required, 
of the MLG forward stabilizer brace.
    Revision 1 of this [Canadian] AD mandated installation of an 
Elbow Restrictor (P/N 46610-1) to the MLG Down-lock Actuators as 
terminating action to the repeat inspections in Part I. The repeat 
inspections in Part IV are required for all Forward Stabilizer Brace 
Assemblies (P/N 46401-7) after Installation of the Elbow Restrictor 
(P/N 46610-1).
    Revision 2 of this [Canadian] AD, in Part III, gives credit for 
the accomplishment of earlier revisions of Bombardier Service 
Bulletin SB 84-32-69 and clarifies, in Part IV, when the initial and 
repeat inspections are required following the installation of the 
elbow restrictor (P/N 46610-1) in Part III of this [Canadian] AD.

    Required actions include repetitive inspections for damage of 
certain MLG forward stabilizer brace assemblies, repetitive inspections 
for cracking of both MLG forward stabilizer braces, applicable liquid 
penetrant inspections for cracking, applicable corrective actions 
including repair or replacement if necessary, rework of the MLG forward 
stabilizer brace, and installation of an elbow restrictor. 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-2019-
0479.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued Service Bulletin 84-32-69, Revision C, dated 
January 20, 2011. This service information describes procedures for 
installing an elbow restrictor with part number (P/N) 46610-1.
    Bombardier has issued Service Bulletin 84-32-76, Revision B, dated 
August 1, 2018. This service information describes procedures for 
replacing the standard elbow fitting at the retract port of the lock 
actuator with a new custom elbow fitting.
    Bombardier has also issued Q400 All Operator Message 338, dated 
February 23, 2009, which the Director of the Federal Register approved 
for incorporation by reference as of May 6, 2009 (74 FR 18121, April 
21, 2009).
    Bombardier has issued Repair Drawing 8/4-32-099, Issue 4, dated 
September 4, 2018. This service information describes procedures for a 
nondestructive inspection for damage (including excessive wear, 
corrosion, foreign object damage, and cracking) of the MLG forward 
stabilizer brace assembly, P/N 46401-7.
    Goodrich has issued Service Concession Request 026-09, Revision H, 
dated August 29, 2018. This service information describes procedures 
for a nondestructive inspection for damage of the MLG forward 
stabilizer brace assembly, P/N 46401-7, and applicable corrective 
actions.
    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.

FAA's Determination

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to the FAA's bilateral agreement with the State of Design Authority, 
the FAA has been notified of the unsafe condition described in the MCAI 
and service information referenced above. The FAA is proposing this AD 
because the FAA evaluated all the relevant information and determined 
the unsafe condition described previously is likely to exist or develop 
on other products of the same type design.

Proposed Requirements of This NPRM

    This proposed AD would retain all requirements of AD 2009-09-02. 
This proposed AD would also require accomplishing the actions specified 
in the service information described previously.

Costs of Compliance

    The FAA estimates that this proposed AD affects 54 airplanes of 
U.S. registry.
    The FAA estimates the following costs to comply with this proposed 
AD:

[[Page 33187]]



                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2009-09-02...  8 work-hours x $85 per                $0            $680         $36,720
                                         hour = $680.
New proposed actions..................  19 work-hours x $85 per           10,867          12,482         674,028
                                         hour = $1,615.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data that would enable the 
agency to provide cost estimates for the on-condition actions specified 
in this proposed AD.
    According to the manufacturer, some or all of the costs of this 
proposed AD may be covered under warranty, thereby reducing the cost 
impact on affected individuals. The FAA does not control warranty 
coverage for affected individuals. As a result, the FAA has included 
all known costs in the cost estimate.

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.
    The FAA is 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.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes and associated appliances to the 
Director of the System Oversight Division.

Regulatory Findings

    The FAA 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) Will not affect intrastate aviation in Alaska, 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.

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 removing Airworthiness Directive (AD) 
2009-09-02, Amendment 39-15888 (74 FR 18121, April 21, 2009), and 
adding the following new AD:

Bombardier, Inc.: Docket No. FAA-2019-0479; Product Identifier 2019-
NM-020-AD.

(a) Comments Due Date

    The FAA must receive comments by August 26, 2019.

(b) Affected ADs

    This AD replaces AD 2009-09-02, Amendment 39-15888 (74 FR 18121, 
April 21, 2009) (``AD 2009-09-02'').

(c) Applicability

    This AD applies to Bombardier, Inc., Model DHC-8-400, -401, and 
-402 airplanes, certificated in any category, serial numbers 4001, 
4003, and subsequent, equipped with main landing gear (MLG) forward 
stabilizer brace part number (P/N) 46401-7.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Main landing 
gear.

(e) Reason

    This AD was prompted by reports of failures of the aft hinge of 
the MLG forward stabilizer brace due to fatigue cracks. The FAA is 
issuing this AD to address failure of the stabilizer brace, which 
could result in the collapse of the MLG.

(f) Compliance

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

(g) Retained Inspection and Corrective Actions, With Revised Service 
Information and Removed Reporting Requirement

    This paragraph restates the requirements of paragraph (f) of AD 
2009-09-02, with new service information and removed reporting 
requirement. Unless already done, do the following actions:
    (1) At the applicable time specified in paragraph (g)(1)(i), 
(g)(1)(ii), (g)(1)(iii), or (g)(1)(iv) of this AD: Perform non-
destructive inspections for damage of the MLG forward stabilizer 
brace assemblies P/N 46401-7, in accordance with Bombardier Repair 
Drawing 8/4-32-099, Issue 1, dated March 10, 2009, and Goodrich 
Service Concession Request 026-09, Revision B, dated March 10, 2009; 
or Bombardier Repair Drawing 8/4-32-099, Issue 4, dated September 4, 
2018, and Goodrich Service Concession Request 026-09, Revision H, 
dated August 29, 2018. Repeat the inspection thereafter at intervals 
not to exceed 2,000 flight cycles. As of the effective date of this 
AD, use Bombardier Repair Drawing 8/4-32-099, Issue 4, dated 
September 4, 2018, and Goodrich Service Concession Request 026-09, 
Revision H, dated August 29, 2018, for the actions required by this 
paragraph.
    (i) For airplanes with MLG forward stabilizer braces that have 
accumulated 12,000 or more total flight cycles as of May 6, 2009 
(the effective date of AD 2009-09-02): Inspect within 50 flight 
cycles after May 6, 2009.
    (ii) For airplanes with MLG forward stabilizer braces that have 
accumulated 9,000 or more total flight cycles but fewer than 12,000 
total flight cycles as of May 6, 2009 (the effective date of AD 
2009-09-02): Inspect before the accumulation of 12,050 total flight 
cycles, or within 500 flight cycles after May 6, 2009, whichever 
occurs earlier.
    (iii) For airplanes with MLG forward stabilizer braces that have 
accumulated 4,500 or more total flight cycles but fewer than 9,000 
total flight cycles as of May 6, 2009 (the effective date of AD 
2009-09-02): Inspect before the accumulation of 9,500 total flight

[[Page 33188]]

cycles, or within 1,500 flight cycles after May 6, 2009, whichever 
occurs earlier.
    (iv) For airplanes with MLG forward stabilizer braces that have 
accumulated fewer than 4,500 total flight cycles as of May 6, 2009 
(the effective date of AD 2009-09-02): Inspect before the 
accumulation of 6,000 total flight cycles.
    (2) If any damage is found during any inspection required by 
paragraph (g)(1) of this AD, before further flight, do all 
applicable corrective actions in accordance with Goodrich Service 
Concession Request 026-09, Revision B, dated March 10, 2009; or 
Goodrich Service Concession Request 026-09, Revision H, dated August 
29, 2018; except as provided by paragraphs (g)(3), (g)(4), (g)(5), 
and (g)(6) of this AD. As of the effective date of this AD, use 
Goodrich Service Concession Request 026-09, Revision H, dated August 
29, 2018, for the actions required by this paragraph.
    (3) For airplanes on which step 24. of Goodrich Service 
Concession Request 026-09, Revision B, dated March 10, 2009, has 
been done: Within 1,200 flight cycles after May 6, 2009 (the 
effective date of AD 2009-09-02), rework the MLG forward stabilizer 
brace, and except for airplanes on which the rework has been done, 
within 600 flight cycles after May 6, 2009, do a detailed visual 
inspection for damage of the stabilizer brace apex lugs, in 
accordance with Goodrich Service Concession Request 026-09, Revision 
B, dated March 10, 2009; or Goodrich Service Concession Request 026-
09, Revision H, dated August 29, 2018. If any damage is found, 
repair before further flight in accordance with Section C of 
Goodrich Service Concession Request 026-09, Revision B, dated March 
10, 2009; or Section C of Goodrich Service Concession Request 026-
09, Revision H, dated August 29, 2018. As of the effective date of 
this AD, use Goodrich Service Concession Request 026-09, Revision H, 
dated August 29, 2018, for the actions required by this paragraph.
    (4) At the applicable time specified in paragraph (g)(4)(i), 
(g)(4)(ii), or (g)(4)(iii) of this AD, replace the forward 
stabilizer brace assembly, in accordance with Goodrich Service 
Concession Request 026-09, Revision B, dated March 10, 2009; or 
Goodrich Service Concession Request 026-09, Revision H, dated August 
29, 2018. As of the effective date of this AD, use Goodrich Service 
Concession Request 026-09, Revision H, dated August 29, 2018, for 
the actions required by this paragraph.
    (i) For airplanes on which cracking is found during any 
inspection required by this AD, and the cracking exceeds the limit 
specified in paragraph (g)(4)(i)(A) or (g)(4)(i)(B) of this AD, as 
applicable: Replace the assembly before further flight.
    (A) For cracking found before the effective date of this AD: The 
limit specified in Section C of Goodrich Service Concession Request 
026-09, Revision B, dated March 10, 2009.
    (B) For cracking found on or after the effective date of this 
AD: The limit specified in Section C or Section D of Goodrich 
Service Concession Request 026-09, Revision H, dated August 29, 
2018.
    (ii) For airplanes on which any cracking is found after the 
rework specified in Section C of Goodrich Service Concession Request 
026-09, Revision B, dated March 10, 2009; or specified in Section C 
or Section D of Goodrich Service Concession Request 026-09, Revision 
H, dated August 29, 2018: Replace the assembly before further 
flight.
    (iii) For airplanes on which no cracking is found after the 
rework specified in Section C of Goodrich Service Concession Request 
026-09, Revision B, dated March 10, 2009; or specified in Section C 
or Section D of Goodrich Service Concession Request 026-09, Revision 
H, dated August 29, 2018: Replace the assembly within 2,700 flight 
cycles after doing the rework.
    (5) If foreign object damage is found during any inspection 
required by this AD, or if damage is found to a forward stabilizer 
brace lug or stop bracket retention hole apex bushing, before 
further flight, repair using a method approved by the Manager, New 
York ACO Branch, FAA; or Transport Canada Civil Aviation (TCCA); or 
Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If 
approved by the DAO, the approval must include the DAO-authorized 
signature.
    (6) If any crack is found during the visual inspection under 10X 
magnification, repair before further flight, in accordance with 
Goodrich Service Concession Request 026-09, Revision B, dated March 
10, 2009; or Goodrich Service Concession Request 026-09, Revision H, 
dated August 29, 2018. As of the effective date of this AD, use 
Goodrich Service Concession Request 026-09, Revision H, dated August 
29, 2018, for the actions required by this paragraph.
    (7) Before the accumulation of 6,000 total flight cycles on the 
MLG forward stabilizer braces, or within 600 flight hours after May 
6, 2009 (the effective date of AD 2009-09-02), whichever occurs 
later: Do a detailed visual inspection for cracking of both MLG 
forward stabilizer braces and do all applicable liquid penetrant 
inspections for cracking, in accordance with Bombardier Q400 All 
Operator Message 338, dated February 23, 2009. Repeat the inspection 
thereafter at intervals not to exceed 600 flight hours. If any 
cracking is found during any inspection required by this paragraph, 
repair before further flight in accordance with Bombardier Repair 
Drawing 8/4-32-099, Issue 1, dated March 10, 2009, and Goodrich 
Service Concession Request 026-09, Revision B, dated March 10, 2009; 
or Bombardier Repair Drawing 8/4-32-099, Issue 4, dated September 4, 
2018, and Goodrich Service Concession Request 026-09, Revision H, 
dated August 29, 2018. As of the effective date of this AD, use 
Bombardier Repair Drawing 8/4-32-099, Issue 4, dated September 4, 
2018, and Goodrich Service Concession Request 026-09, Revision H, 
dated August 29, 2018, to repair cracking found during any 
inspection required by this paragraph.

(h) New Requirement of This AD: Installation of Elbow Restrictor

    Within 2,000 flight hours or 12 months, whichever occurs first, 
from the effective date of this AD: Install an elbow restrictor, P/N 
46610-1, in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 84-32-69, Revision C, dated January 20, 
2011.

(i) Terminating Actions

    (1) Installation of an elbow restrictor as required by paragraph 
(h) of this AD terminates the repetitive inspection requirements of 
paragraphs (g)(1) and (g)(7) of this AD.
    (2) Installation of an elbow restrictor as required by paragraph 
(h) of this AD terminates the replacement of the forward stabilizer 
brace assembly requirement of paragraph (g)(4)(iii) of this AD.

(j) New Requirement of This AD: Revised Repetitive Inspections of the 
MLG Forward Stabilizer Brace

    (1) Within 2,000 flight cycles after the installation specified 
in paragraph (h) of this AD, or within 12 months after the effective 
date, whichever occurs later, do the non-destructive inspection, in 
accordance with Bombardier Repair Drawing 8/4-32-099, Issue 4, dated 
September 4, 2018, and Goodrich Service Concession Request 026-09, 
Revision H, dated August 29, 2018. Thereafter, repeat the non-
destructive inspection at the times specified in paragraph (j)(2) of 
this AD.
    (2) Repeat the non-destructive inspection required in paragraph 
(j)(1) of this AD at the applicable intervals specified in 
paragraphs (j)(2)(i), (j)(2)(ii), and (j)(2)(iii) of this AD.
    (i) For forward stabilizer braces, P/N 46401-7, that have not 
had any required rework done, as specified in Goodrich Service 
Concession Request 026-09, Section C or D, and have had Bombardier 
Service Bulletin 84-32-69 or Bombardier Service Bulletin 84-32-76 
incorporated: Do the non-destructive inspection at intervals not to 
exceed 6,000 flight cycles.
    (ii) For forward stabilizer braces, P/N 46401-7, that have been 
reworked in accordance with Goodrich Service Concession Request 026-
09, Section D, and have had Bombardier Service Bulletin 84-32-69 or 
Bombardier Service Bulletin 84-32-76 incorporated: Do the non-
destructive inspection at intervals not to exceed 6,000 flight 
cycles.
    (iii) For forward stabilizer braces, P/N 46401-7, that have been 
reworked in accordance with Goodrich Service Concession Request 026-
09, Section C, and have had Bombardier Service Bulletin 84-32-69 or 
Bombardier Service Bulletin 84-32-76 incorporated: Do the non-
destructive inspection at intervals not to exceed 3,000 flight 
cycles.

(k) Acceptable Method of Compliance for Paragraph (h) of This AD

    Replacing the standard elbow fitting at the retract port of the 
lock actuator with a new custom elbow fitting in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-32-76, 
Revision B, dated August 1, 2018, is an acceptable method of 
compliance for the installation required by paragraph (h) of this 
AD.

(l) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using the service information in paragraph 
(l)(1)(i), (l)(1)(ii), or (l)(1)(iii) of this AD.

[[Page 33189]]

    (i) Bombardier Service Bulletin 84-32-69, dated June 30, 2009.
    (ii) Bombardier Service Bulletin 84-32-69, Revision A, dated 
August 19, 2009.
    (iii) Bombardier Service Bulletin 84-32-69, Revision B, dated 
September 17, 2009.
    (2) This paragraph provides credit for actions specified in 
paragraph (j) of this AD, if those actions were performed before the 
effective date of this AD using the service information in paragraph 
(l)(2)(i), (l)(2)(ii), or (l)(2)(iii) of this AD.
    (i) Bombardier Repair Drawing 8/4-32-099, Issue 1, dated March 
10, 2009, and Goodrich Service Concession Request 026-09, Revision 
B, dated March 10, 2009.
    (ii) Bombardier Repair Drawing 8/4-32-099, Issue 2, dated April 
20, 2009, and Goodrich Service Concession Request 026-09, Revision 
C, dated April 17, 2009.
    (iii) Bombardier Repair Drawing 8/4-32-099, Issue 3, dated 
December 3, 2009, and Goodrich Service Concession Request 026-09, 
Revision D, dated November 27, 2009.
    (3) This paragraph provides credit for actions performed using 
the method of compliance specified in paragraph (k) of this AD, if 
those actions were performed before the effective date of this AD 
using the service information in paragraph (l)(3)(i) or (l)(3)(ii) 
of this AD.
    (i) Bombardier Service Bulletin 84-32-76, dated May 20, 2010.
    (ii) Bombardier Service Bulletin 84-32-76, Revision A, dated 
June 19, 2014.

(m) Other FAA AD Provisions

    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York ACO Branch, 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 certification 
office, send it to ATTN: Program Manager, Continuing Operational 
Safety, FAA, New York ACO Branch. AMOCs approved previously in 
accordance with AD 2009-09-02 are approved as AMOCs for the 
corresponding requirements in paragraph (g) of 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 
Branch, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO. If approved by 
the DAO, the approval must include the DAO-authorized signature.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian AD CF-2009-11R2, dated May 31, 2018, 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-2019-0479.
    (2) For more information about this AD, contact Andrea Jimenez, 
Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, 
New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; telephone 516-228-7330; fax 516-794-5531; email [email protected].
    (3) 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 [email protected]; internet 
https://www.bombardier.com. For Goodrich service information 
identified in this NPRM, contact Collins Aerospace, 1400 South 
Service Road West, Oakville, Ontario L6L 5Y7, Canada; telephone: 
905-827-7777. You may view this service information at the FAA, 
Transport Standards Branch, 2200 South 216th St., Des Moines, WA. 
For information on the availability of this material at the FAA, 
call 206-231-3195.

    Issued in Des Moines, Washington, on June 26, 2019.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-14045 Filed 7-11-19; 8:45 am]
BILLING CODE 4910-13-P

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