Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes, 66582-66586 [2019-26232]

Download as PDF 66582 Federal Register / Vol. 84, No. 234 / Thursday, December 5, 2019 / Rules and Regulations Airworthiness Limitations Section (ALS) Part 2–Damage Tolerant Airworthiness Limitation Items (DT–ALI), Revision 07, dated June 13, 2018. The initial compliance time for doing the tasks is at the time specified in Airbus A318/A319/A320/A321 Airworthiness Limitations Section (ALS) Part 2–Damage Tolerant Airworthiness Limitation Items (DT–ALI), Revision 07, dated June 13, 2018, or within 90 days after the effective date of this AD, whichever occurs later. (h) No Alternative Actions or Intervals After the existing maintenance or inspection program has been revised as required by paragraph (g) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (j)(1) of this AD. (i) Terminating Action for AD 2018–25–02 Accomplishing the actions required by this AD terminates all requirements of AD 2018– 25–02. jbell on DSKJLSW7X2PROD with RULES (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards 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 International Section, send it to the attention of the person identified in paragraph (k)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. (i) 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. (ii) AMOCs approved previously for AD 2018–25–02 are approved as AMOCs for the corresponding provisions of this AD, provided there is no change in description, threshold and interval of the applicable tasks. (iii) AMOC AIR–676–19–235, dated June 3, 2019, is approved as an AMOC for the corresponding provisions 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, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2018–0288, dated December 21, 2018, for related information. This MCAI may be found in the AD docket on the internet at https:// VerDate Sep<11>2014 16:17 Dec 04, 2019 Jkt 250001 www.regulations.gov by searching for and locating Docket No. FAA–2019–0321. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206– 231–3223. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus A318/A319/A320/A321 Airworthiness Limitations Section (ALS) Part 2–Damage Tolerant Airworthiness Limitation Items (DT–ALI), Revision 07, dated June 13, 2018. (ii) [Reserved] (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EIAS, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; internet https://www.airbus.com. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. The FAA is superseding Airworthiness Directive (AD) 2009–09– 02, which applied to certain Bombardier, Inc., Model DHC–8–400 series airplanes. AD 2009–09–02 required 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. This AD retains the existing actions and also requires installation of an elbow restrictor. 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 the unsafe condition on these products. SUMMARY: This AD is effective January 9, 2020. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 9, 2020. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of May 6, 2009 (74 FR 18121, April 21, 2009). DATES: DEPARTMENT OF TRANSPORTATION For service information identified in this final rule, contact De Havilland Aircraft of Canada Limited, Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375– 4000; fax 416–375–4539; email thd@ dehavilland.com; internet https:// dehavilland.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–2019–0479. Federal Aviation Administration Examining the AD Docket 14 CFR Part 39 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 final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. Issued in Des Moines, Washington, on November 7, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–26231 Filed 12–4–19; 8:45 am] BILLING CODE 4910–13–P [Docket No. FAA–2019–0479; Product Identifier 2019–NM–020–AD; Amendment 39–19790; AD 2019–22–11] RIN 2120–AA64 Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 ADDRESSES: E:\FR\FM\05DER1.SGM 05DER1 Federal Register / Vol. 84, No. 234 / Thursday, December 5, 2019 / Rules and Regulations 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: Discussion Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian AD CF–2009–11R2, dated May 31, 2018 (also referred to as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc., Model DHC–8–400 series airplanes. 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. The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2009–09–02, Amendment 39–15888 (74 FR 18121, April 21, 2009) (‘‘AD 2009–09–02’’). AD 2009–09–02 applied to certain Bombardier Model DHC–8–400 series airplanes. The NPRM published in the Federal Register on July 12, 2019 (84 FR 33185). The NPRM was prompted by reports of failures of the aft hinge of the MLG forward stabilizer brace due to fatigue cracks. The NPRM proposed to continue to require 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. The NPRM also proposed to require installation of an elbow restrictor. The FAA is issuing this AD to address failure of the stabilizer brace, which could result in the collapse of the MLG. See the MCAI for additional background information. Comments The FAA gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA’s response to each comment. Support for the NPRM Air Line Pilots Association, International (ALPA) stated its support for the NPRM. Request To Exclude Certain Service Information Procedures Horizon Air requested that paragraphs (h) and (k) of the proposed AD refer specifically to paragraph 3.B., ‘‘Procedure,’’ in the Accomplishment Instructions of the referenced service information rather than ‘‘the Accomplishment Instructions.’’ Horizon Air stated that the ‘‘Job-Set Up’’ and ‘‘Close Out’’ procedures in the Accomplishment Instructions of the applicable service information do not directly correct the unsafe condition. The FAA agrees with the commenter’s request for the reason provided above. The FAA has revised paragraphs (h) and (k) of this AD to require accomplishment of paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of the applicable service information. Explanation of Additional Change Made to This Final Rule The FAA has revised this final rule to identify the legal name of the manufacturer, De Havilland Aircraft of Canada Limited, as published in the most recent type certificate data sheet for the affected airplane model. Conclusion The FAA reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule with the changes described previously and minor editorial changes. The FAA has determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. The FAA also determined that these changes will not increase the economic 66583 burden on any operator or increase the scope of this final rule. Related Service Information Under 1 CFR Part 51 Bombardier has issued the following service information. • Bombardier Service Bulletin 84–32– 69, Revision C, dated January 20, 2011, which describes procedures for replacing the standard elbow fitting with a new restrictor elbow fitting. • Bombardier Service Bulletin 84–32– 76, Revision B, dated August 1, 2018, which describes procedures for replacing the standard elbow fitting with a new restrictor elbow fitting and introduction of a new configuration stabilizer brace assembly. • Bombardier Repair Drawing 8/4– 32–099, Issue 4, dated September 4, 2018, which describes, among other actions, procedures for inspections for cracking of the apex lug stop on the MLG forward stabilizer brace assembly. • UTC Aerospace Systems Service Concession Request 026–09, Revision H, dated August 29, 2018, which describes, among other actions, procedures for inspections for excessive wear of the apex pins on the MLG forward stabilizer brace assembly. This AD also requires the following service information, which the Director of the Federal Register approved for incorporation by reference as of May 6, 2009 (75 FR 18121, April 21, 2009). • Bombardier Q400 All Operator Message 338, dated February 23, 2009. • Bombardier Repair Drawing 8/4– 32–099, Issue 1, dated March 10, 2009. • Goodrich Service Concession Request 026–09, Revision B, dated March 10, 2009. 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. Costs of Compliance The FAA estimates that this AD affects 54 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: jbell on DSKJLSW7X2PROD with RULES ESTIMATED COSTS FOR REQUIRED ACTIONS Action Labor cost Retained actions from AD 2009–09–02 ......... New actions .................................................... 8 work-hours × $85 per hour = $680 ............. 19 work-hours × $85 per hour = $1,615 ........ VerDate Sep<11>2014 16:17 Dec 04, 2019 Jkt 250001 PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 Parts cost $0 10,867 E:\FR\FM\05DER1.SGM 05DER1 Cost per product $680 12,482 Cost on U.S. operators $36,720 674,028 66584 Federal Register / Vol. 84, No. 234 / Thursday, December 5, 2019 / Rules and Regulations The FAA has received no definitive data that would enable it to provide cost estimates for the on-condition actions specified in this AD. According to the manufacturer, some or all of the costs of this 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. jbell on DSKJLSW7X2PROD with RULES 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 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 AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and VerDate Sep<11>2014 16:17 Dec 04, 2019 Jkt 250001 (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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2009–09–02, Amendment 39–15888 (74 FR 18121, April 21, 2009), and adding the following new AD: ■ 2019–22–11 De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.): Amendment 39–19790; Docket No. FAA–2019–0479; Product Identifier 2019–NM–020–AD. (a) Effective Date This AD is effective January 9, 2020. (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 De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by 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. PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 (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 one of paragraphs (g)(1)(i) through (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 UTC Aerospace Systems 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 UTC Aerospace Systems 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 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 UTC Aerospace Systems Service Concession Request 026–09, Revision H, dated August 29, 2018; except as provided by paragraphs (g)(3) through (6) of this AD. As of the effective date of this AD, use UTC Aerospace Systems 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– E:\FR\FM\05DER1.SGM 05DER1 jbell on DSKJLSW7X2PROD with RULES Federal Register / Vol. 84, No. 234 / Thursday, December 5, 2019 / Rules and Regulations 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 UTC Aerospace Systems 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 UTC Aerospace Systems Service Concession Request 026–09, Revision H, dated August 29, 2018. As of the effective date of this AD, use UTC Aerospace Systems 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 one of paragraphs (g)(4)(i) through (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 UTC Aerospace Systems Service Concession Request 026–09, Revision H, dated August 29, 2018. As of the effective date of this AD, use UTC Aerospace Systems 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 (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 UTC Aerospace Systems 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 UTC Aerospace Systems 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 UTC Aerospace Systems 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); or De VerDate Sep<11>2014 16:17 Dec 04, 2019 Jkt 250001 Havilland Aircraft of Canada Limited’s TCCA 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 UTC Aerospace Systems Service Concession Request 026–09, Revision H, dated August 29, 2018. As of the effective date of this AD, use UTC Aerospace Systems 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 UTC Aerospace Systems 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 UTC Aerospace Systems 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 paragraph 3.B., ‘‘Procedure,’’ of 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 (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 PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 66585 Bombardier Repair Drawing 8/4–32–099, Issue 4, dated September 4, 2018, and UTC Aerospace Systems Service Concession Request 026–09, Revision H, dated August 29, 2018. Thereafter, repeat the nondestructive 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) through (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 or UTC Aerospace Systems 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 or UTC Aerospace Systems 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 nondestructive 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 or UTC Aerospace Systems 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 nondestructive 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 paragraph 3.B., ‘‘Procedure,’’ of 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 one of paragraphs (l)(1)(i) through (iii) of this AD. (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 one of paragraphs (l)(2)(i) through (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 E:\FR\FM\05DER1.SGM 05DER1 66586 Federal Register / Vol. 84, No. 234 / Thursday, December 5, 2019 / Rules and Regulations 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 (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; or De Havilland Aircraft of Canada Limited’s TCCA DAO. If approved by the DAO, the approval must include the DAOauthorized signature. jbell on DSKJLSW7X2PROD with RULES (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 9-avs-nyaco-cos@faa.gov. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(5) and (6) of this AD. (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. VerDate Sep<11>2014 16:17 Dec 04, 2019 Jkt 250001 (3) The following service information was approved for IBR on January 9, 2020. (i) Bombardier Repair Drawing 8/4–32– 099, Issue 4, dated September 4, 2018. (ii) Bombardier Service Bulletin 84–32–69, Revision C, dated January 20, 2011. (iii) Bombardier Service Bulletin 84–32–76, Revision B, dated August 1, 2018. (iv) UTC Aerospace Systems Service Concession Request 026–09, Revision H, dated August 29, 2018. (4) The following service information was approved for IBR on May 6, 2009 (75 FR 18121, April 21, 2009). (i) Bombardier Q400 All Operator Message 338, dated February 23, 2009. The issue date is specified on only the first page of this document. (ii) Bombardier Repair Drawing 8/4–32– 099, Issue 1, dated March 10, 2009. The issue date is specified on only the first page of this document. (iii) Goodrich Service Concession Request 026–09, Revision B, dated March 10, 2009. Pages 1 through 8 of this document are identified as Revision B, dated March 5, 2009; pages 9 through 22 are identified as Revision B, dated March 10, 2009. (5) For service information identified in this AD, contact De Havilland Aircraft of Canada Limited, Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416– 375–4000; fax 416–375–4539; email thd@ dehavilland.com; internet https:// dehavilland.com. (6) 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. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@nara.gov, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on November 7, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–26232 Filed 12–4–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF DEFENSE Department of the Navy 32 CFR Part 775 [Docket No. USN–2018–HQ–0001] RIN 0703–AB01 Policies and Responsibilities for Implementation of the National Environmental Policy Act Within the Department of the Navy Department of the Navy, Department of Defense. AGENCY: PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 ACTION: Final rule. The Department of the Navy (DON) revises portions of its internal regulations that establish the responsibilities and procedures for complying with the National Environmental Policy Act (NEPA). An agency may determine that certain classes of actions normally do not individually or cumulatively have significant environmental impacts and therefore do not require further review under NEPA. Establishing these categories of activities, called categorical exclusions (CATEXs), in the agency’s NEPA implementing procedures is a way to reduce unnecessary paperwork and delay. This revision clarifies what types of activities fall under CATEXs and normally do not require additional NEPA analysis. DATES: Effective January 6, 2020. FOR FURTHER INFORMATION CONTACT: Mr. J. Dan Cecchini, Office of the Deputy Assistant Secretary of the Navy (Environment), 703–614–1173. SUPPLEMENTARY INFORMATION: SUMMARY: Process Used by the DON in the Development of the Proposed Revisions In 2015, the Office of the Deputy Assistant Secretary of the Navy for Environment directed a review of 32 CFR 775.6(e) and (f), which address the DON’s procedures for applying CATEXs. A review panel (hereinafter ‘‘panel’’) was formed to provide administrative support and expertise to inform the efforts. The professionals comprising the panel were current DON environmental practitioners with numerous years of NEPA planning and compliance experience, including the preparation of environmental documentation such as CATEX decision documents, environmental assessments (EAs), environmental impact statements (EISs), findings of no significant impact, and records of decision. The panel was supported by a legal working group comprising experienced environmental law attorneys from the DON’s Office of the General Counsel and Office of the Judge Advocate General with advanced education and experience providing legal and policy advice to Federal agency decision makers, managers, and practitioners on environmental planning and compliance responsibilities. The panel reviewed and analyzed the supporting rationale, scope, applicability, and wording of each existing CATEX and extraordinary circumstance set forth in 32 CFR 775.6(e) and (f). The panel developed and deliberated on each proposed new CATEX and extraordinary circumstance E:\FR\FM\05DER1.SGM 05DER1

Agencies

[Federal Register Volume 84, Number 234 (Thursday, December 5, 2019)]
[Rules and Regulations]
[Pages 66582-66586]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-26232]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0479; Product Identifier 2019-NM-020-AD; Amendment 
39-19790; AD 2019-22-11]
RIN 2120-AA64


Airworthiness Directives; De Havilland Aircraft of Canada Limited 
(Type Certificate Previously Held by Bombardier, Inc.) Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2009-09-
02, which applied to certain Bombardier, Inc., Model DHC-8-400 series 
airplanes. AD 2009-09-02 required 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. This AD retains the existing actions and also 
requires installation of an elbow restrictor. 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 the 
unsafe condition on these products.

DATES: This AD is effective January 9, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 9, 
2020.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of May 6, 
2009 (74 FR 18121, April 21, 2009).

ADDRESSES: For service information identified in this final rule, 
contact De Havilland Aircraft of Canada Limited, 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://dehavilland.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-2019-0479.

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 final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations is U.S. Department 
of Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

[[Page 66583]]


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: 

Discussion

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD CF-2009-11R2, dated May 
31, 2018 (also referred to as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition for 
certain Bombardier, Inc., Model DHC-8-400 series airplanes. 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.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2009-09-02, Amendment 39-15888 (74 FR 
18121, April 21, 2009) (``AD 2009-09-02''). AD 2009-09-02 applied to 
certain Bombardier Model DHC-8-400 series airplanes. The NPRM published 
in the Federal Register on July 12, 2019 (84 FR 33185). The NPRM was 
prompted by reports of failures of the aft hinge of the MLG forward 
stabilizer brace due to fatigue cracks. The NPRM proposed to continue 
to require 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. The NPRM also proposed to require installation of 
an elbow restrictor. The FAA is issuing this AD to address failure of 
the stabilizer brace, which could result in the collapse of the MLG. 
See the MCAI for additional background information.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The following presents the comments 
received on the NPRM and the FAA's response to each comment.

Support for the NPRM

    Air Line Pilots Association, International (ALPA) stated its 
support for the NPRM.

Request To Exclude Certain Service Information Procedures

    Horizon Air requested that paragraphs (h) and (k) of the proposed 
AD refer specifically to paragraph 3.B., ``Procedure,'' in the 
Accomplishment Instructions of the referenced service information 
rather than ``the Accomplishment Instructions.'' Horizon Air stated 
that the ``Job-Set Up'' and ``Close Out'' procedures in the 
Accomplishment Instructions of the applicable service information do 
not directly correct the unsafe condition.
    The FAA agrees with the commenter's request for the reason provided 
above. The FAA has revised paragraphs (h) and (k) of this AD to require 
accomplishment of paragraph 3.B., ``Procedure,'' of the Accomplishment 
Instructions of the applicable service information.

Explanation of Additional Change Made to This Final Rule

    The FAA has revised this final rule to identify the legal name of 
the manufacturer, De Havilland Aircraft of Canada Limited, as published 
in the most recent type certificate data sheet for the affected 
airplane model.

Conclusion

    The FAA reviewed the relevant data, considered the comments 
received, and determined that air safety and the public interest 
require adopting this final rule with the changes described previously 
and minor editorial changes. The FAA has determined that these minor 
changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    The FAA also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this final 
rule.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued the following service information.
     Bombardier Service Bulletin 84-32-69, Revision C, dated 
January 20, 2011, which describes procedures for replacing the standard 
elbow fitting with a new restrictor elbow fitting.
     Bombardier Service Bulletin 84-32-76, Revision B, dated 
August 1, 2018, which describes procedures for replacing the standard 
elbow fitting with a new restrictor elbow fitting and introduction of a 
new configuration stabilizer brace assembly.
     Bombardier Repair Drawing 8/4-32-099, Issue 4, dated 
September 4, 2018, which describes, among other actions, procedures for 
inspections for cracking of the apex lug stop on the MLG forward 
stabilizer brace assembly.
     UTC Aerospace Systems Service Concession Request 026-09, 
Revision H, dated August 29, 2018, which describes, among other 
actions, procedures for inspections for excessive wear of the apex pins 
on the MLG forward stabilizer brace assembly.
    This AD also requires the following service information, which the 
Director of the Federal Register approved for incorporation by 
reference as of May 6, 2009 (75 FR 18121, April 21, 2009).
     Bombardier Q400 All Operator Message 338, dated February 
23, 2009.
     Bombardier Repair Drawing 8/4-32-099, Issue 1, dated March 
10, 2009.
     Goodrich Service Concession Request 026-09, Revision B, 
dated March 10, 2009.
    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.

Costs of Compliance

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

                                      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 actions...........................  19 work-hours x $85 per           10,867          12,482         674,028
                                         hour = $1,615.
----------------------------------------------------------------------------------------------------------------


[[Page 66584]]

    The FAA has received no definitive data that would enable it to 
provide cost estimates for the on-condition actions specified in this 
AD.
    According to the manufacturer, some or all of the costs of this 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 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 AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2009-09-02, Amendment 39-15888 (74 FR 18121, April 21, 2009), and 
adding the following new AD:

2019-22-11 De Havilland Aircraft of Canada Limited (Type Certificate 
Previously Held by Bombardier, Inc.): Amendment 39-19790; Docket No. 
FAA-2019-0479; Product Identifier 2019-NM-020-AD.

(a) Effective Date

    This AD is effective January 9, 2020.

(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 De Havilland Aircraft of Canada Limited (Type 
Certificate Previously Held by 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 one of paragraphs 
(g)(1)(i) through (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 UTC Aerospace Systems 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 UTC Aerospace Systems 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 
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 UTC 
Aerospace Systems Service Concession Request 026-09, Revision H, 
dated August 29, 2018; except as provided by paragraphs (g)(3) 
through (6) of this AD. As of the effective date of this AD, use UTC 
Aerospace Systems 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-

[[Page 66585]]

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 UTC Aerospace Systems 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 UTC Aerospace Systems Service Concession Request 026-
09, Revision H, dated August 29, 2018. As of the effective date of 
this AD, use UTC Aerospace Systems 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 one of paragraphs 
(g)(4)(i) through (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 UTC Aerospace 
Systems Service Concession Request 026-09, Revision H, dated August 
29, 2018. As of the effective date of this AD, use UTC Aerospace 
Systems 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 (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 UTC Aerospace 
Systems 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 UTC Aerospace Systems 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 UTC Aerospace Systems 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); or De 
Havilland Aircraft of Canada Limited's TCCA 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 UTC Aerospace Systems Service Concession Request 026-
09, Revision H, dated August 29, 2018. As of the effective date of 
this AD, use UTC Aerospace Systems 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 UTC Aerospace Systems 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 UTC Aerospace Systems 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 paragraph 3.B., ``Procedure,'' of 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 (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 UTC Aerospace Systems 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) through (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 or UTC 
Aerospace Systems 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 or UTC Aerospace Systems 
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 or UTC Aerospace Systems 
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 
paragraph 3.B., ``Procedure,'' of 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 one of 
paragraphs (l)(1)(i) through (iii) of this AD.
    (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 one of 
paragraphs (l)(2)(i) through (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

[[Page 66586]]

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 (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; or De 
Havilland Aircraft of Canada Limited'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) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(5) and (6) of this AD.

(o) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
January 9, 2020.
    (i) Bombardier Repair Drawing 8/4-32-099, Issue 4, dated 
September 4, 2018.
    (ii) Bombardier Service Bulletin 84-32-69, Revision C, dated 
January 20, 2011.
    (iii) Bombardier Service Bulletin 84-32-76, Revision B, dated 
August 1, 2018.
    (iv) UTC Aerospace Systems Service Concession Request 026-09, 
Revision H, dated August 29, 2018.
    (4) The following service information was approved for IBR on 
May 6, 2009 (75 FR 18121, April 21, 2009).
    (i) Bombardier Q400 All Operator Message 338, dated February 23, 
2009. The issue date is specified on only the first page of this 
document.
    (ii) Bombardier Repair Drawing 8/4-32-099, Issue 1, dated March 
10, 2009. The issue date is specified on only the first page of this 
document.
    (iii) Goodrich Service Concession Request 026-09, Revision B, 
dated March 10, 2009. Pages 1 through 8 of this document are 
identified as Revision B, dated March 5, 2009; pages 9 through 22 
are identified as Revision B, dated March 10, 2009.
    (5) For service information identified in this AD, contact De 
Havilland Aircraft of Canada Limited, 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://dehavilland.com.
    (6) 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on November 7, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-26232 Filed 12-4-19; 8:45 am]
 BILLING CODE 4910-13-P