2021-20-21: Engine Controls, Propeller Governor

1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. 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. (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 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., Beranových 65, 199 02 Praha 9, Let?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