Airworthiness Directives; GE Aviation Czech s.r.o. (Type Certificate Previously Held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.) Turboprop Engines, 60550-60554 [2021-23879]

Download as PDF 60550 § 590.530 Federal Register / Vol. 86, No. 210 / Wednesday, November 3, 2021 / Rules and Regulations [Removed] 3. Effective October 31, 2022, remove § 590.530. ■ § 590.536 ■ [Amended] 4. Add § 590.536 to read as follows: § 590.536 Freezing operations. (a) [Reserved] (b)(1) Nonpasteurized egg products which are to be frozen shall be solidly frozen or reduced to a temperature of 10 °F or lower within 60 hours from time of breaking. (2) Pasteurized egg products which are to be frozen shall be solidly frozen or reduced to a temperature of 10 °F or lower within 60 hours from time of pasteurization. (3) The temperature of the products not solidly frozen shall be taken at the center of the container to determine compliance with this section. (c) through (e) [Reserved] § 590.536 [Removed] 5. Effective October 31, 2022, remove § 590.536. ■ Done at Washington, DC. Theresa Nintemann, Deputy Administrator. [FR Doc. 2021–23703 Filed 11–2–21; 8:45 am] BILLING CODE 3410–DM–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0836; Project Identifier MCAI–2020–01629–E; Amendment 39–21759; AD 2021–20–21] RIN 2120–AA64 Airworthiness Directives; GE Aviation Czech s.r.o. (Type Certificate Previously Held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.) Turboprop Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2018–16– 10 which applied to certain GE Aviation Czech s.r.o. (GEAC) H80–200 model turboprop engines. AD 2018–16–10 required an adjustment of the engine push-pull control and replacement of the beta switch to prevent the propeller governor control from going to a negative thrust position. This AD requires an initial inspection and adjustment of the engine push-pull khammond on DSKJM1Z7X2PROD with RULES SUMMARY: VerDate Sep<11>2014 15:53 Nov 02, 2021 Jkt 256001 control and replacement of the beta switch. This AD also requires inspection and adjustment of the engine push-pull control after any maintenance, repair or modification that affects the push-pull control and installation of an improved push-pull control. This AD also expands the applicability to include GEAC H85– 200 model turboprop engines with Avia Propeller AV–725 propellers installed. This AD was prompted by an accident involving an Aircraft Industries (AI) L 410 UVP–E20 airplane caused by one propeller going to a negative thrust position during the landing approach. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective November 18, 2021. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 18, 2021. The FAA must receive any comments on this AD by December 20, 2021. 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 service information identified in this final rule, contact GE Aviation Czech s.r.o., Beranovy´ch 65, 199 02 Praha 9, Letnˇany, Czech Republic; phone: +420 222 538 111. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (781) 238– 7759. It is also available at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 0836. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0836; 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 mandatory continuing airworthiness information (MCAI), any PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 comments received, and other information. The street address for the Docket Operations is listed above. FOR FURTHER INFORMATION CONTACT: Barbara Caufield, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7146; fax: (781) 238– 7199; email: barbara.caufield@faa.gov. SUPPLEMENTARY INFORMATION: Background The FAA issued AD 2018–16–10, Amendment 39–19350 (83 FR 43742, August 28, 2018) (AD 2018–16–10), for certain GE Aviation Czech H80–200 model turboprop engines. AD 2018–16– 10 required replacement of the beta switch and adjustment of the engine push-pull control to prevent the propeller governor control from going to a negative thrust position. AD 2018–16– 10 resulted from an accident involving an AI L 410 UVP–E20 airplane caused by one propeller going to a negative thrust position during the landing approach. The FAA issued AD 2018– 16–10 to require engine modification to prevent asymmetric thrust. The unsafe condition, if not addressed, could result in failure of the beta switch, loss of engine thrust control, and reduced control of the airplane. Actions Since AD 2018–16–10 Was Issued Since the FAA issued AD 2018–16– 10, the European Union Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2020–0143, dated June 25, 2020, to address an unsafe condition for the specified products. The MCAI states: In 2017, a fatal accident was reported of an L 410 UVP–E20 aeroplane. The investigation determined that there was an annunciation of Beta mode on the right-hand engine, that the propeller went inadvertently beyond the fine pitch position and reached a negative thrust position, and that the pitch lock system did not intervene. The event occurred on approach at a speed and altitude which did not allow the flight crew to recover this control system malfunction. This condition, if not corrected, could lead to reduced control or loss of control of the aeroplane. To address this unsafe condition, GEAC issued the SB, providing inspection and modification instructions, and EASA issued AD 2018–0075 to require a one-time inspection and adjustment of the engine push-pull control and replacement of the beta switch with an improved part. Addressing the same unsafe condition at aeroplane level, EASA also issued AD 2018– 0057, requiring modification of affected AI L 410 UVP–E20 and L 410 UVP–E20 CARGO aeroplanes, if equipped with H80–200 E:\FR\FM\03NOR1.SGM 03NOR1 Federal Register / Vol. 86, No. 210 / Wednesday, November 3, 2021 / Rules and Regulations engines and Avia Propeller AV 725 propellers. After EASA AD 2018–0075 was issued, it was identified that the engine push-pull control settings may be inadvertently changed after certain maintenance, repair, or modification action. For that reason, the engine push-pull control needed further inspection and adjustment. Affected maintenance, repair, or modification procedures include, but are not limited to, the replacement of a fuel control unit or a propeller governor. Furthermore, it was determined that H85–200 engines are also affected by the new requirements. Consequently, EASA issued AD 2019–0089, retaining the requirements of EASA AD 2018–0075, which was superseded, and requiring conditional repetitive inspections and, depending on findings, adjustment of the push-pull control settings. That [EASA] AD also expanded the applicability to include H85–200 engines. After EASA AD 2019–0089 was issued, GEAC developed an improved engine pushpull control which reduces further the risk of uncommanded in-flight reverse of the propeller, and published the original issue of the ASB–2. Consequently, EASA issued AD 2019–0244, retaining the requirements of EASA AD 2019–0089, which was superseded, and requiring installation of the new engine push-pull controls. That [EASA] AD also required inspections of modified engines. Since that [EASA] AD was issued, based on the field experience gained from the inspections and replacements of Push-Pull Control System performed in accordance with the ASB–2 revision 03, GEAC issued the ASB–2 (now at revision 04), as defined in this [EASA] AD, which provides additional clarifications and more accurate description of the adjustments of the controls and regulation and engine testing after hardware replacement. The ASB–2 also improves the sequence of steps, thus helping to prevent erroneous accomplishment of the inspection and modification instructions. It has also been determined that for certain engines no repetitive inspections are required. For the reason described above, this [EASA] AD partially retains the requirements of EASA AD 2019–0244, which is superseded, but requires accomplishment of required actions in accordance with the improved GEAC instructions. khammond on DSKJM1Z7X2PROD with RULES You may obtain further information by examining the MCAI in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0836. The FAA is issuing this AD to address the unsafe condition on these products. FAA’s Determination This product has been approved by EASA and is approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with the European Community, EASA has notified us of the unsafe condition described in the MCAI. The FAA is issuing this AD because the agency evaluated the VerDate Sep<11>2014 15:53 Nov 02, 2021 Jkt 256001 60551 relevant information provided by EASA and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Group 5 engines. This AD does not specify allowances, as it simply allows installation of engines with push-pull control P/N M601–76.5 or M601–76.4, as applicable, installed. Related Service Information Under 1 CFR Part 51 The FAA reviewed GEAC Service Bulletin (SB) SB–H80–76–00–00–0036 [02], Revision No. 02, dated March 29, 2018; GEAC SB SB–H80–76–00–00– 0036 [03], Revision No. 03, dated April 12, 2019; and GEAC Alert SB ASB– H80–76–00–00–0048[01]/ASB–H85–76– 00–00–0015 [01] (single document, formatted as service bulletin identifier [revision number]), dated April 12, 2019. The SBs and the Alert SB, differentiated by affected engine model, describe procedures for inspecting and adjusting the engine push-pull control, part number (P/N) M601–76.3. The SBs also describe procedures for replacing beta switch, P/N P–S–2, with beta switch, P/N P–S–2A. The Alert SB also adds GEAC H85–200 model turboprop engines to its effectivity. The FAA also reviewed GEAC Alert SB ASB–H80–76–00–00–0047[04]/ASB– H85–76–00–00–0018[04] (single document, formatted as service bulletin identifier [revision number]), dated May 8, 2020. The Alert SB describes procedures for replacing and inspecting the engine push-pull control system. The FAA also reviewed Section 72– 00–00, Engine—Planned Inspections, dated December 14, 2012; of the GE Aviation—Business & General Aviation—Turboprops Maintenance Manual, Manual Part No. 0983402, Rev. 22, dated December 18, 2020 (the GE Aviation Maintenance Manual). Section 72–00–00 of the GE Aviation Maintenance Manual describes procedures for performing Type 2 and Type 3 inspections. 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 ADDRESSES. Justification for Immediate Adoption and Determination of the Effective Date Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 U.S.C. 551 et seq.) authorizes agencies to dispense with notice and comment procedures for rules when the agency, for ‘‘good cause,’’ finds that those procedures are ‘‘impracticable, unnecessary, or contrary to the public interest.’’ Under this section, an agency, upon finding good cause, may issue a final rule without providing notice and seeking comment prior to issuance. Further, section 553(d) of the APA authorizes agencies to make rules effective in less than thirty days, upon a finding of good cause. The FAA justifies waiving notice and comment prior to adoption of this rule because no domestic operators use this product. Accordingly, notice and opportunity for prior public comment are unnecessary, pursuant to 5 U.S.C. 553(b)(3)(B). In addition, for the foregoing reason, the FAA finds that good cause exists pursuant to 5 U.S.C. 553(d) for making this amendment effective in less than 30 days. AD Requirements This AD requires inspection and adjustment of the engine push-pull control, replacement of certain beta switches, inspection and adjustment of the engine push-pull control after any maintenance, repair or modification action that affects the push-pull control, and installation of an improved pushpull control. Differences Between This AD and the MCAI or Service Information EASA AD 2020–0143 specifies installation allowances for Group 4 and PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 Comments Invited The FAA invites you to send any written data, views, or arguments about this final rule. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2021–0836 and Project Identifier MCAI–2020– 01629–E’’ at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this final rule because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this final rule. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act E:\FR\FM\03NOR1.SGM 03NOR1 60552 Federal Register / Vol. 86, No. 210 / Wednesday, November 3, 2021 / Rules and Regulations (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this AD contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this AD, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this AD. Submissions containing CBI should be sent to Barbara Caufield, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. Regulatory Flexibility Act The requirements of the Regulatory Flexibility Act (RFA) do not apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt a rule without prior notice and comment. Because FAA has determined that it has good cause to adopt this rule without prior notice and comment, RFA analysis is not required. Costs of Compliance The FAA estimates that this AD affects 0 engines installed on airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS Cost per product Parts cost Cost on U.S. operators Action Labor cost Inspect and adjust push-pull control after any maintenance, repair or modification. Inspect and adjust push-pull control and replace beta switch. Install push-pull control ................................... 4 work-hours × $85 per hour = $340 ............. $0 $340 $0 8 work-hours × $85 per hour = $680 ............. 1,916 2,596 0 4 work-hours × $85 per hour = $340 ............. 5,525 5,865 0 The FAA estimates the following costs to do any necessary replacements that would be required based on the results of the inspection. The FAA has no way of determining the number of aircraft that might need these replacements. khammond on DSKJM1Z7X2PROD with RULES ON-CONDITION COSTS Cost per product Action Labor cost Inspect push-pull control (paragraphs (g)(6) through (8)). Remove and replace beta switch (paragraph (g)(6)) ... Adjust push-pull control (paragraph (g)(6)) .................. 2 work-hours × $85 per hour = $170 ........................... $0 $170 4 work-hours × $85 per hour = $340 ........................... 3 work-hours × $85 per hour = $255 ........................... 1,916 0 2,256 255 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. 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, and (2) Will not affect intrastate aviation in Alaska. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a PART 39—AIRWORTHINESS DIRECTIVES VerDate Sep<11>2014 15:53 Nov 02, 2021 Jkt 256001 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: 1. The authority citation for part 39 continues to read as follows: ■ PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Parts cost Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by: a. Removing Airworthiness Directive 2018–16–10, Amendment 39–19350 (83 FR 43742, August 28, 2018); and ■ b. Adding the following new airworthiness directive: ■ ■ 2021–20–21 GE Aviation Czech s.r.o. (Type Certificate previously held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.): Amendment 39– 21759; Docket No. FAA–2021–0836; Project Identifier MCAI–2020–01629–E. (a) Effective Date This airworthiness directive (AD) is effective November 18, 2021. (b) Affected ADs This AD replaces AD 2018–16–10, Amendment 39–19350 (83 FR 43742, August 28, 2018) (AD 2018–16–10). (c) Applicability This AD applies to: (1) GE Aviation Czech s.r.o. (GEAC) H80– 200 model turboprop engines with propeller governor part number (P/N) P–W22–1, and Avia Propeller AV–725 propellers installed. E:\FR\FM\03NOR1.SGM 03NOR1 Federal Register / Vol. 86, No. 210 / Wednesday, November 3, 2021 / Rules and Regulations (2) GEAC H85–200 model turboprop engines (build configuration BC04) with Avia Propeller AV–725 propellers installed. (d) Subject Joint Aircraft System Component (JASC) Code 7600, Engine Controls; 6122, Propeller Governor. (e) Unsafe Condition This AD was prompted by an accident involving an Aircraft Industries L 410 UVP– E20 airplane caused by one propeller going to a negative thrust position during the landing approach. The FAA is issuing this AD to prevent asymmetric thrust. The unsafe condition, if not addressed, could result in failure of the beta switch, loss of engine thrust control, and reduced control of the airplane. khammond on DSKJM1Z7X2PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For Group 1 engines: Within 25 flight hours (FHs) or 20 flight cycles after September 12, 2018 (the effective date of AD 2018–16–10), or before further flight, whichever occurs later, inspect and adjust the engine push-pull control, P/N M601– 76.3, and replace beta switch, P/N P–S–2, with beta switch, P/N P–S–2A, using paragraphs 1.6 and 1.7 of GEAC Service Bulletin (SB) SB–H80–76–00–00–0036 [03], (formatted as service bulletin identifier [revision number]), dated April 12, 2019 (GEAC SB SB–H80–76–00–00–0036 [03]) or paragraphs 1.6 and 1.7 of GEAC SB–H80–76– 00–00–0036 [02], Revision No. 02, dated March 29, 2018. (2) For Group 1, Group 2, and Group 3 engines: Before further flight after any maintenance, repair, or modification on the engine, propeller, or airplane that can affect the settings of the engine push-pull control after the effective date of this AD, inspect and adjust the engine push-pull control, P/N M601–76.3, using paragraph 1.6 of GEAC Alert Service Bulletin (ASB) ASB–H80–76– 00–00–0048[01]/ASB–H85–76–00–00–0015 [01] (single document, formatted as service bulletin identifier [revision number]), dated April 12, 2019 (GEAC ASB ASB–H80–76–00– 00–0048[01]/ASB–H85–76–00–00–0015 [01]). (3) For Group 1, Group 2, and Group 3 engines: Within 270 days after the effective date of this AD, replace the engine push-pull control, P/N M601–76.3, with engine pushpull control P/N M601–76.4 or P/N M601– 76.5, as applicable to the engine model, using Appendix 1 of GEAC ASB ASB–H80–76–00– 00–0047[04]/ASB–H85–76–00–00–0018[04] (single document, formatted as service bulletin identifier [revision number]), dated May 8, 2020 (GEAC ASB ASB–H80–76–00– 00–0047[04]/ASB–H85–76–00–00–0018[04]). (4) For engines modified as required by paragraph (g)(3) of this AD: Within 100 FHs or during a subsequent Type 2 inspection, whichever occurs first after the engine modification required by paragraph (g)(3) of this AD, and thereafter, at intervals not to exceed 100 FHs from the previous inspection, inspect the engine push-pull VerDate Sep<11>2014 15:53 Nov 02, 2021 Jkt 256001 control, P/N M601–76.4 or P/N M601–76.5, using the Accomplishment Instructions, paragraph 2.1.2, of GEAC ASB–H80–76–00– 00–0047[04]/ASB–H85–76–00–00–0018[04]. Note 1 to paragraph (g)(4): A noncumulative tolerance of 10 FH may be applied to the 100 FH repetitive inspection interval to allow synchronization of the required checks with other required maintenance tasks for which a noncumulative tolerance is already granted in the applicable engine maintenance manual (EMM). (5) For all affected engines not required to be modified as specified in paragraph (g)(3) of this AD: Within 300 FHs or at the next Type 3 inspection, whichever occurs later since first installation of the engine on an airplane, inspect the engine push-pull control, P/N M601–76.4 or P/N M601–76.5, as applicable, using the instructions in Table 601 (Sheet 1–4) of Section 72–00–00, dated December 14, 2012, of the GE Aviation— Business & General Aviation—Turboprops Maintenance Manual, Manual Part No. 0983402, Rev. 22, dated December 18, 2020 (the GE Aviation Maintenance Manual). (6) If, during any inspection required by paragraph (g)(1) or (2) of this AD, as applicable, any deficiencies are detected, before next flight, perform the actions in paragraphs 1.6.2, 1.7.1 and 1.7.2 of GEAC SB SB–H80–76–00–00–0036 [03] or paragraph 1.6.1 of GEAC ASB ASB–H80–76–00–00– 0048[01]/ASB–H85–76–00–00–0015 [01], as applicable. (7) If, during any inspection required by paragraph (g)(4) of this AD, any deficiencies are detected, before next flight, perform the actions in paragraph 2.1.2 of GEAC ASB ASB–H80–76–00–00–0047[04]/ASB–H85– 76–00–00–0018[04]. (8) If, during the inspection as required by paragraph (g)(5) of this AD, any deficiencies are detected, before next flight, correct those deficiencies using the instructions in Table 601 (Sheet 1–4), Section 72–00–00, Engine— Planned Inspections, dated December 14, 2012, of the GE Aviation Maintenance Manual. (h) Installation Prohibition After the effective date of this AD: (1) For Group 1 engines: Do not install a beta switch, P/N P–S–2, on any engine, after modification of the engine as required by paragraph (g)(1) of this AD. (2) For Group 2, Group 3, Group 4, and Group 5 engines: Do not install a beta switch, P/N P–S–2, on any engine. (3) For Group 1, Group 2, and Group 3 engines: Do not install an engine push-pull control, P/N M601–76.3, on any engine after modification of the engine as required by paragraph (g)(3) of this AD. (i) Terminating Action Accomplishing the inspection of the engine push-pull control, P/N M601–76.4 or P/N M601–76.5, as required by paragraph (g)(4) of this AD, without finding any deficiencies during six consecutive inspections, constitutes a terminating action for the repetitive inspections required by paragraph (g)(4) of this AD for that engine. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 60553 (j) No Communication or Reporting Requirements The instructions to contact the manufacturer for further instructions in paragraph 2.1, of GEAC ASB ASB–H80–76– 00–00–0047[04]/ASB–H85–76–00–00– 0018[04], are not required by this AD. (k) Definitions (1) Group 1 engines are GEAC H80–200 model turboprop engines that have an engine push-pull control, P/N M601–76.3, and a beta switch, P/N P–S–2, installed. (2) Group 2 engines are GEAC H80–200 model turboprop engines that have an engine push-pull control, P/N M601–76.3, but no beta switch, P/N P–S–2, installed. (3) Group 3 engines are GEAC H85–200 model turboprop engines (build configuration BC04) that have an engine push-pull control, P/N M601–76.3, installed. (4) Group 4 engines are GEAC H80–200 model turboprop engines that have an engine push-pull control, P/N M601–76.5, installed. (5) Group 5 engines are GEAC H85–200 model turboprop engines (build configuration BC04) that have an engine push-pull control, P/N M601–76.4, installed. (6) For the purpose of this AD, ‘‘deficiencies’’ occur when the push-pull control settings are changed, thereby allowing the propeller to go beyond fine pitch into negative thrust position during certain engine failure modes. (l) Credit for Previous Actions (1) You may take credit for the inspection and adjustment of the engine push-pull control required by paragraph (g)(2) of this AD if you performed the actions before the effective date of this AD using GEAC ASB– H80–76–00–00–0048[00]/ASB–H85–76–00– 00–0015[00] (single document), dated April 12, 2019. (2) You may take credit for the installation of the engine push-pull control required by paragraph (g)(3) of this AD and the initial inspection of the engine push-pull control required by paragraph (g)(4) of this AD, if you performed these actions before the effective date of this AD using GEAC ASB ASB–H80– 76–00–00–0047[03]/ASB–H85–76–00–00– 0018[03] (single document), Revision No. 03, dated August 7, 2019, or earlier revisions. (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO 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 ECO Branch, send it to the attention of the person identified in paragraph (n)(1) of this AD. You may email your request to: ANE-AD-AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (n) Related Information (1) For more information about this AD, contact Barbara Caufield, Aviation Safety E:\FR\FM\03NOR1.SGM 03NOR1 60554 Federal Register / Vol. 86, No. 210 / Wednesday, November 3, 2021 / Rules and Regulations Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7146; fax: (781) 238–7199; email: barbara.caufield@faa.gov. (2) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2020–0143, dated June 25, 2020, for related information. This MCAI may be found in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA– 2021–0836. (o) Material Incorporated by Reference khammond on DSKJM1Z7X2PROD with RULES (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 the AD specifies otherwise. (i) GE Aviation Czech (GEAC) Service Bulletin (SB) SB–H80–76–00–00–0036 [02], Revision No. 02, dated March 29, 2018. (ii) GEAC SB SB–H80–76–00–00–0036 [03], Revision No. 03, dated April 12, 2019. (iii) GEAC Alert SB ASB–H80–76–00–00– 0048[01]/ASB–H85–76–00–00–0015 [01] (single document), Revision No. 01, dated April 12, 2019. (iv) GEAC Alert SB ASB–H80–76–00–00– 0047[04]/ASB–H85–76–00–00–0018 [04] (single document), Revision No. 04, dated May 8, 2020. (v) Section 72–00–00, pages 603 through 605, dated December 14, 2012; and page 606, dated December 18, 2020, of GE Aviation Business & General Aviation—Turboprops Maintenance Manual, Manual Part No. 0983402, Rev. 22, dated December 18, 2020. (3) For GEAC and GE Aviation service information identified in this AD, contact GE Aviation Czech s.r.o., Beranovy´ch 65, 199 02 Praha 9, Letnˇany, Czech Republic; phone: +420 222 538 111. (4) You may view this service information at FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (781) 238–7759. (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, email: fr.inspection@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued on September 23, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–23879 Filed 11–2–21; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 15:53 Nov 02, 2021 Jkt 256001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0560; Project Identifier MCAI–2021–00192–T; Amendment 39–21764; AD 2021–21–04] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD–700–1A10 and BD–700–1A11 airplanes. This AD was prompted by reports that the sliding bushings in the forward engine mount system were missing. This AD requires an inspection (gap check) of the front and aft engine mounts to verify the proper installation of the sliding bushings, and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective December 8, 2021. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 8, 2021. ADDRESSES: For service information identified in this final rule, contact Bombardier, Inc., 200 Coˆte-Vertu Road West, Dorval, Que´bec H4S 2A3, Canada; telephone 514–855–2999; email ac.yul@ aero.bombardier.com; internet https:// www.bombardier.com. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety 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–2021–0560. SUMMARY: 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–2021– 0560; 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, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Elizabeth Dowling, Aerospace Engineer, Mechanical Systems and Administrative Services Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531; email 9-avs-nyaco-cos@faa.gov. SUPPLEMENTARY INFORMATION: Background Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued TCCA AD CF– 2021–04, dated February 15, 2021 (also referred to as the Mandatory Continuing Airworthiness Information, or the MCAI), to correct an unsafe condition for certain Bombardier, Inc., Model BD– 700–1A10 and BD–700–1A11 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–2021– 0560. The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Bombardier, Inc., Model BD–700–1A10 and BD–700–1A11 airplanes. The NPRM published in the Federal Register on July 9, 2021 (86 FR 36243). The NPRM was prompted by reports that the sliding bushings in the forward engine mount system were missing. The NPRM proposed to require an inspection (gap check) of the front and aft engine mounts to verify the proper installation of the sliding bushings, and repair if necessary. The FAA is issuing this AD to address redistribution of load/stress on the mount components, which may decrease the component fatigue life; failure of the mount structural components could result in the loss of the engine attachment to the airframe. 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 comment received on the NPRM and the FAA’s response to the comment. Request To Update Certain Service Information and Provide Credit for Actions Accomplished Using Previous Service Information Bombardier, Inc., stated that Bombardier Service Bulletin 700–71– 005, dated December 14, 2020, has been updated to Bombardier Service Bulletin 700–71–005, Revision 01, dated April E:\FR\FM\03NOR1.SGM 03NOR1

Agencies

[Federal Register Volume 86, Number 210 (Wednesday, November 3, 2021)]
[Rules and Regulations]
[Pages 60550-60554]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-23879]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0836; Project Identifier MCAI-2020-01629-E; 
Amendment 39-21759; AD 2021-20-21]
RIN 2120-AA64


Airworthiness Directives; GE Aviation Czech s.r.o. (Type 
Certificate Previously Held by WALTER Engines a.s., Walter a.s., and 
MOTORLET a.s.) Turboprop Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2018-16-10 
which applied to certain GE Aviation Czech s.r.o. (GEAC) H80-200 model 
turboprop engines. AD 2018-16-10 required an adjustment of the engine 
push-pull control and replacement of the beta switch to prevent the 
propeller governor control from going to a negative thrust position. 
This AD requires an initial inspection and adjustment of the engine 
push-pull control and replacement of the beta switch. This AD also 
requires inspection and adjustment of the engine push-pull control 
after any maintenance, repair or modification that affects the push-
pull control and installation of an improved push-pull control. This AD 
also expands the applicability to include GEAC H85-200 model turboprop 
engines with Avia Propeller AV-725 propellers installed. This AD was 
prompted by an accident involving an Aircraft Industries (AI) L 410 
UVP-E20 airplane caused by one propeller going to a negative thrust 
position during the landing approach. The FAA is issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective November 18, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 18, 
2021.
    The FAA must receive any comments on this AD by December 20, 2021.

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 service information identified in this final rule, contact GE 
Aviation Czech s.r.o., Beranov[yacute]ch 65, 199 02 Praha 9, 
Let[ncaron]any, Czech Republic; phone: +420 222 538 111. You may view 
this service information at the FAA, Airworthiness Products Section, 
Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. 
For information on the availability of this material at the FAA, call 
(781) 238-7759. It is also available at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0836.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0836; 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 
mandatory continuing airworthiness information (MCAI), any comments 
received, and other information. The street address for the Docket 
Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Barbara Caufield, Aviation Safety 
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; 
phone: (781) 238-7146; fax: (781) 238-7199; email: 
[email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued AD 2018-16-10, Amendment 39-19350 (83 FR 43742, 
August 28, 2018) (AD 2018-16-10), for certain GE Aviation Czech H80-200 
model turboprop engines. AD 2018-16-10 required replacement of the beta 
switch and adjustment of the engine push-pull control to prevent the 
propeller governor control from going to a negative thrust position. AD 
2018-16-10 resulted from an accident involving an AI L 410 UVP-E20 
airplane caused by one propeller going to a negative thrust position 
during the landing approach. The FAA issued AD 2018-16-10 to require 
engine modification to prevent asymmetric thrust. The unsafe condition, 
if not addressed, could result in failure of the beta switch, loss of 
engine thrust control, and reduced control of the airplane.

Actions Since AD 2018-16-10 Was Issued

    Since the FAA issued AD 2018-16-10, the European Union Aviation 
Safety Agency (EASA), which is the Technical Agent for the Member 
States of the European Community, has issued EASA AD 2020-0143, dated 
June 25, 2020, to address an unsafe condition for the specified 
products. The MCAI states:

    In 2017, a fatal accident was reported of an L 410 UVP-E20 
aeroplane. The investigation determined that there was an 
annunciation of Beta mode on the right-hand engine, that the 
propeller went inadvertently beyond the fine pitch position and 
reached a negative thrust position, and that the pitch lock system 
did not intervene. The event occurred on approach at a speed and 
altitude which did not allow the flight crew to recover this control 
system malfunction.
    This condition, if not corrected, could lead to reduced control 
or loss of control of the aeroplane.
    To address this unsafe condition, GEAC issued the SB, providing 
inspection and modification instructions, and EASA issued AD 2018-
0075 to require a one-time inspection and adjustment of the engine 
push-pull control and replacement of the beta switch with an 
improved part. Addressing the same unsafe condition at aeroplane 
level, EASA also issued AD 2018-0057, requiring modification of 
affected AI L 410 UVP-E20 and L 410 UVP-E20 CARGO aeroplanes, if 
equipped with H80-200

[[Page 60551]]

engines and Avia Propeller AV 725 propellers.
    After EASA AD 2018-0075 was issued, it was identified that the 
engine push-pull control settings may be inadvertently changed after 
certain maintenance, repair, or modification action. For that 
reason, the engine push-pull control needed further inspection and 
adjustment. Affected maintenance, repair, or modification procedures 
include, but are not limited to, the replacement of a fuel control 
unit or a propeller governor. Furthermore, it was determined that 
H85-200 engines are also affected by the new requirements. 
Consequently, EASA issued AD 2019-0089, retaining the requirements 
of EASA AD 2018-0075, which was superseded, and requiring 
conditional repetitive inspections and, depending on findings, 
adjustment of the push-pull control settings. That [EASA] AD also 
expanded the applicability to include H85-200 engines.
    After EASA AD 2019-0089 was issued, GEAC developed an improved 
engine push-pull control which reduces further the risk of 
uncommanded in-flight reverse of the propeller, and published the 
original issue of the ASB-2. Consequently, EASA issued AD 2019-0244, 
retaining the requirements of EASA AD 2019-0089, which was 
superseded, and requiring installation of the new engine push-pull 
controls. That [EASA] AD also required inspections of modified 
engines.
    Since that [EASA] AD was issued, based on the field experience 
gained from the inspections and replacements of Push-Pull Control 
System performed in accordance with the ASB-2 revision 03, GEAC 
issued the ASB-2 (now at revision 04), as defined in this [EASA] AD, 
which provides additional clarifications and more accurate 
description of the adjustments of the controls and regulation and 
engine testing after hardware replacement. The ASB-2 also improves 
the sequence of steps, thus helping to prevent erroneous 
accomplishment of the inspection and modification instructions. It 
has also been determined that for certain engines no repetitive 
inspections are required.
    For the reason described above, this [EASA] AD partially retains 
the requirements of EASA AD 2019-0244, which is superseded, but 
requires accomplishment of required actions in accordance with the 
improved GEAC instructions.

    You may obtain further information by examining the MCAI in the AD 
docket at https://www.regulations.gov by searching for and locating 
Docket No. FAA-2021-0836.
    The FAA is issuing this AD to address the unsafe condition on these 
products.

FAA's Determination

    This product has been approved by EASA and is approved for 
operation in the United States. Pursuant to the FAA's bilateral 
agreement with the European Community, EASA has notified us of the 
unsafe condition described in the MCAI. The FAA is issuing this AD 
because the agency evaluated the relevant information provided by EASA 
and determined the unsafe condition described previously is likely to 
exist or develop in other products of the same type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed GEAC Service Bulletin (SB) SB-H80-76-00-00-0036 
[02], Revision No. 02, dated March 29, 2018; GEAC SB SB-H80-76-00-00-
0036 [03], Revision No. 03, dated April 12, 2019; and GEAC Alert SB 
ASB-H80-76-00-00-0048[01]/ASB-H85-76-00-00-0015 [01] (single document, 
formatted as service bulletin identifier [revision number]), dated 
April 12, 2019. The SBs and the Alert SB, differentiated by affected 
engine model, describe procedures for inspecting and adjusting the 
engine push-pull control, part number (P/N) M601-76.3. The SBs also 
describe procedures for replacing beta switch, P/N P-S-2, with beta 
switch, P/N P-S-2A. The Alert SB also adds GEAC H85-200 model turboprop 
engines to its effectivity.
    The FAA also reviewed GEAC Alert SB ASB-H80-76-00-00-0047[04]/ASB-
H85-76-00-00-0018[04] (single document, formatted as service bulletin 
identifier [revision number]), dated May 8, 2020. The Alert SB 
describes procedures for replacing and inspecting the engine push-pull 
control system.
    The FAA also reviewed Section 72-00-00, Engine--Planned 
Inspections, dated December 14, 2012; of the GE Aviation--Business & 
General Aviation--Turboprops Maintenance Manual, Manual Part No. 
0983402, Rev. 22, dated December 18, 2020 (the GE Aviation Maintenance 
Manual). Section 72-00-00 of the GE Aviation Maintenance Manual 
describes procedures for performing Type 2 and Type 3 inspections.
    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 ADDRESSES.

AD Requirements

    This AD requires inspection and adjustment of the engine push-pull 
control, replacement of certain beta switches, inspection and 
adjustment of the engine push-pull control after any maintenance, 
repair or modification action that affects the push-pull control, and 
installation of an improved push-pull control.

Differences Between This AD and the MCAI or Service Information

    EASA AD 2020-0143 specifies installation allowances for Group 4 and 
Group 5 engines. This AD does not specify allowances, as it simply 
allows installation of engines with push-pull control P/N M601-76.5 or 
M601-76.4, as applicable, installed.

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and 
comment procedures for rules when the agency, for ``good cause,'' finds 
that those procedures are ``impracticable, unnecessary, or contrary to 
the public interest.'' Under this section, an agency, upon finding good 
cause, may issue a final rule without providing notice and seeking 
comment prior to issuance. Further, section 553(d) of the APA 
authorizes agencies to make rules effective in less than thirty days, 
upon a finding of good cause.
    The FAA justifies waiving notice and comment prior to adoption of 
this rule because no domestic operators use this product. Accordingly, 
notice and opportunity for prior public comment are unnecessary, 
pursuant to 5 U.S.C. 553(b)(3)(B). In addition, for the foregoing 
reason, the FAA finds that good cause exists pursuant to 5 U.S.C. 
553(d) for making this amendment effective in less than 30 days.

Comments Invited

    The FAA invites you to send any written data, views, or arguments 
about this final rule. Send your comments to an address listed under 
ADDRESSES. Include ``Docket No. FAA-2021-0836 and Project Identifier 
MCAI-2020-01629-E'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
this final rule because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this final rule.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act

[[Page 60552]]

(FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your 
comments responsive to this AD contain commercial or financial 
information that is customarily treated as private, that you actually 
treat as private, and that is relevant or responsive to this AD, it is 
important that you clearly designate the submitted comments as CBI. 
Please mark each page of your submission containing CBI as ``PROPIN.'' 
The FAA will treat such marked submissions as confidential under the 
FOIA, and they will not be placed in the public docket of this AD. 
Submissions containing CBI should be sent to Barbara Caufield, Aviation 
Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 
01803. Any commentary that the FAA receives which is not specifically 
designated as CBI will be placed in the public docket for this 
rulemaking.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because FAA has determined 
that it has good cause to adopt this rule without prior notice and 
comment, RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 0 engines installed on 
airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspect and adjust push-pull control    4 work-hours x $85 per                $0            $340              $0
 after any maintenance, repair or        hour = $340.
 modification.
Inspect and adjust push-pull control    8 work-hours x $85 per             1,916           2,596               0
 and replace beta switch.                hour = $680.
Install push-pull control.............  4 work-hours x $85 per             5,525           5,865               0
                                         hour = $340.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary 
replacements that would be required based on the results of the 
inspection. The FAA has no way of determining the number of aircraft 
that might need these replacements.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Inspect push-pull control (paragraphs (g)(6)    2 work-hours x $85 per hour =                 $0            $170
 through (8)).                                   $170.
Remove and replace beta switch (paragraph       4 work-hours x $85 per hour =              1,916           2,256
 (g)(6)).                                        $340.
Adjust push-pull control (paragraph (g)(6))...  3 work-hours x $85 per hour =                  0             255
                                                 $255.
----------------------------------------------------------------------------------------------------------------

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.

Regulatory Findings

    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, and
    (2) Will not affect intrastate aviation in Alaska.

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:
0
a. Removing Airworthiness Directive 2018-16-10, Amendment 39-19350 (83 
FR 43742, August 28, 2018); and
0
b. Adding the following new airworthiness directive:

2021-20-21 GE Aviation Czech s.r.o. (Type Certificate previously 
held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.): 
Amendment 39-21759; Docket No. FAA-2021-0836; Project Identifier 
MCAI-2020-01629-E.

(a) Effective Date

    This airworthiness directive (AD) is effective November 18, 
2021.

(b) Affected ADs

    This AD replaces AD 2018-16-10, Amendment 39-19350 (83 FR 43742, 
August 28, 2018) (AD 2018-16-10).

(c) Applicability

    This AD applies to:
    (1) GE Aviation Czech s.r.o. (GEAC) H80-200 model turboprop 
engines with propeller governor part number (P/N) P-W22-1, and Avia 
Propeller AV-725 propellers installed.

[[Page 60553]]

    (2) GEAC H85-200 model turboprop engines (build configuration 
BC04) with Avia Propeller AV-725 propellers installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7600, Engine 
Controls; 6122, Propeller Governor.

(e) Unsafe Condition

    This AD was prompted by an accident involving an Aircraft 
Industries L 410 UVP-E20 airplane caused by one propeller going to a 
negative thrust position during the landing approach. The FAA is 
issuing this AD to prevent asymmetric thrust. The unsafe condition, 
if not addressed, could result in failure of the beta switch, loss 
of engine thrust control, and reduced control of the airplane.

(f) Compliance

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

(g) Required Actions

    (1) For Group 1 engines: Within 25 flight hours (FHs) or 20 
flight cycles after September 12, 2018 (the effective date of AD 
2018-16-10), or before further flight, whichever occurs later, 
inspect and adjust the engine push-pull control, P/N M601-76.3, and 
replace beta switch, P/N P-S-2, with beta switch, P/N P-S-2A, using 
paragraphs 1.6 and 1.7 of GEAC Service Bulletin (SB) SB-H80-76-00-
00-0036 [03], (formatted as service bulletin identifier [revision 
number]), dated April 12, 2019 (GEAC SB SB-H80-76-00-00-0036 [03]) 
or paragraphs 1.6 and 1.7 of GEAC SB-H80-76-00-00-0036 [02], 
Revision No. 02, dated March 29, 2018.
    (2) For Group 1, Group 2, and Group 3 engines: Before further 
flight after any maintenance, repair, or modification on the engine, 
propeller, or airplane that can affect the settings of the engine 
push-pull control after the effective date of this AD, inspect and 
adjust the engine push-pull control, P/N M601-76.3, using paragraph 
1.6 of GEAC Alert Service Bulletin (ASB) ASB-H80-76-00-00-0048[01]/
ASB-H85-76-00-00-0015 [01] (single document, formatted as service 
bulletin identifier [revision number]), dated April 12, 2019 (GEAC 
ASB ASB-H80-76-00-00-0048[01]/ASB-H85-76-00-00-0015 [01]).
    (3) For Group 1, Group 2, and Group 3 engines: Within 270 days 
after the effective date of this AD, replace the engine push-pull 
control, P/N M601-76.3, with engine push-pull control P/N M601-76.4 
or P/N M601-76.5, as applicable to the engine model, using Appendix 
1 of GEAC ASB ASB-H80-76-00-00-0047[04]/ASB-H85-76-00-00-0018[04] 
(single document, formatted as service bulletin identifier [revision 
number]), dated May 8, 2020 (GEAC ASB ASB-H80-76-00-00-0047[04]/ASB-
H85-76-00-00-0018[04]).
    (4) For engines modified as required by paragraph (g)(3) of this 
AD: Within 100 FHs or during a subsequent Type 2 inspection, 
whichever occurs first after the engine modification required by 
paragraph (g)(3) of this AD, and thereafter, at intervals not to 
exceed 100 FHs from the previous inspection, inspect the engine 
push-pull control, P/N M601-76.4 or P/N M601-76.5, using the 
Accomplishment Instructions, paragraph 2.1.2, of GEAC ASB-H80-76-00-
00-0047[04]/ASB-H85-76-00-00-0018[04].

    Note 1 to paragraph (g)(4):  A non-cumulative tolerance of 10 FH 
may be applied to the 100 FH repetitive inspection interval to allow 
synchronization of the required checks with other required 
maintenance tasks for which a non-cumulative tolerance is already 
granted in the applicable engine maintenance manual (EMM).

    (5) For all affected engines not required to be modified as 
specified in paragraph (g)(3) of this AD: Within 300 FHs or at the 
next Type 3 inspection, whichever occurs later since first 
installation of the engine on an airplane, inspect the engine push-
pull control, P/N M601-76.4 or P/N M601-76.5, as applicable, using 
the instructions in Table 601 (Sheet 1-4) of Section 72-00-00, dated 
December 14, 2012, of the GE Aviation--Business & General Aviation--
Turboprops Maintenance Manual, Manual Part No. 0983402, Rev. 22, 
dated December 18, 2020 (the GE Aviation Maintenance Manual).
    (6) If, during any inspection required by paragraph (g)(1) or 
(2) of this AD, as applicable, any deficiencies are detected, before 
next flight, perform the actions in paragraphs 1.6.2, 1.7.1 and 
1.7.2 of GEAC SB SB-H80-76-00-00-0036 [03] or paragraph 1.6.1 of 
GEAC ASB ASB-H80-76-00-00-0048[01]/ASB-H85-76-00-00-0015 [01], as 
applicable.
    (7) If, during any inspection required by paragraph (g)(4) of 
this AD, any deficiencies are detected, before next flight, perform 
the actions in paragraph 2.1.2 of GEAC ASB ASB-H80-76-00-00-
0047[04]/ASB-H85-76-00-00-0018[04].
    (8) If, during the inspection as required by paragraph (g)(5) of 
this AD, any deficiencies are detected, before next flight, correct 
those deficiencies using the instructions in Table 601 (Sheet 1-4), 
Section 72-00-00, Engine--Planned Inspections, dated December 14, 
2012, of the GE Aviation Maintenance Manual.

(h) Installation Prohibition

    After the effective date of this AD:
    (1) For Group 1 engines: Do not install a beta switch, P/N P-S-
2, on any engine, after modification of the engine as required by 
paragraph (g)(1) of this AD.
    (2) For Group 2, Group 3, Group 4, and Group 5 engines: Do not 
install a beta switch, P/N P-S-2, on any engine.
    (3) For Group 1, Group 2, and Group 3 engines: Do not install an 
engine push-pull control, P/N M601-76.3, on any engine after 
modification of the engine as required by paragraph (g)(3) of this 
AD.

(i) Terminating Action

    Accomplishing the inspection of the engine push-pull control, P/
N M601-76.4 or P/N M601-76.5, as required by paragraph (g)(4) of 
this AD, without finding any deficiencies during six consecutive 
inspections, constitutes a terminating action for the repetitive 
inspections required by paragraph (g)(4) of this AD for that engine.

(j) No Communication or Reporting Requirements

    The instructions to contact the manufacturer for further 
instructions in paragraph 2.1, of GEAC ASB ASB-H80-76-00-00-
0047[04]/ASB-H85-76-00-00-0018[04], are not required by this AD.

(k) Definitions

    (1) Group 1 engines are GEAC H80-200 model turboprop engines 
that have an engine push-pull control, P/N M601-76.3, and a beta 
switch, P/N P-S-2, installed.
    (2) Group 2 engines are GEAC H80-200 model turboprop engines 
that have an engine push-pull control, P/N M601-76.3, but no beta 
switch, P/N P-S-2, installed.
    (3) Group 3 engines are GEAC H85-200 model turboprop engines 
(build configuration BC04) that have an engine push-pull control, P/
N M601-76.3, installed.
    (4) Group 4 engines are GEAC H80-200 model turboprop engines 
that have an engine push-pull control, P/N M601-76.5, installed.
    (5) Group 5 engines are GEAC H85-200 model turboprop engines 
(build configuration BC04) that have an engine push-pull control, P/
N M601-76.4, installed.
    (6) For the purpose of this AD, ``deficiencies'' occur when the 
push-pull control settings are changed, thereby allowing the 
propeller to go beyond fine pitch into negative thrust position 
during certain engine failure modes.

(l) Credit for Previous Actions

    (1) You may take credit for the inspection and adjustment of the 
engine push-pull control required by paragraph (g)(2) of this AD if 
you performed the actions before the effective date of this AD using 
GEAC ASB-H80-76-00-00-0048[00]/ASB-H85-76-00-00-0015[00] (single 
document), dated April 12, 2019.
    (2) You may take credit for the installation of the engine push-
pull control required by paragraph (g)(3) of this AD and the initial 
inspection of the engine push-pull control required by paragraph 
(g)(4) of this AD, if you performed these actions before the 
effective date of this AD using GEAC ASB ASB-H80-76-00-00-0047[03]/
ASB-H85-76-00-00-0018[03] (single document), Revision No. 03, dated 
August 7, 2019, or earlier revisions.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO 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 
ECO Branch, send it to the attention of the person identified in 
paragraph (n)(1) of this AD. You may email your request to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(n) Related Information

    (1) For more information about this AD, contact Barbara 
Caufield, Aviation Safety

[[Page 60554]]

Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 
01803; phone: (781) 238-7146; fax: (781) 238-7199; email: 
[email protected].
    (2) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2020-0143, dated June 25, 2020, for related 
information. This MCAI may be found in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA-
2021-0836.

(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 the AD specifies otherwise.
    (i) GE Aviation Czech (GEAC) Service Bulletin (SB) SB-H80-76-00-
00-0036 [02], Revision No. 02, dated March 29, 2018.
    (ii) GEAC SB SB-H80-76-00-00-0036 [03], Revision No. 03, dated 
April 12, 2019.
    (iii) GEAC Alert SB ASB-H80-76-00-00-0048[01]/ASB-H85-76-00-00-
0015 [01] (single document), Revision No. 01, dated April 12, 2019.
    (iv) GEAC Alert SB ASB-H80-76-00-00-0047[04]/ASB-H85-76-00-00-
0018 [04] (single document), Revision No. 04, dated May 8, 2020.
    (v) Section 72-00-00, pages 603 through 605, dated December 14, 
2012; and page 606, dated December 18, 2020, of GE Aviation Business 
& General Aviation--Turboprops Maintenance Manual, Manual Part No. 
0983402, Rev. 22, dated December 18, 2020.
    (3) For GEAC and GE Aviation service information identified in 
this AD, contact GE Aviation Czech s.r.o., Beranov[yacute]ch 65, 199 
02 Praha 9, Let[ncaron]any, Czech Republic; phone: +420 222 538 111.
    (4) You may view this service information at FAA, Airworthiness 
Products Section, Operational Safety Branch, 1200 District Avenue, 
Burlington, MA 01803. For information on the availability of this 
material at the FAA, call (781) 238-7759.
    (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, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on September 23, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-23879 Filed 11-2-21; 8:45 am]
BILLING CODE 4910-13-P

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