Airworthiness directives › 2021-20-21
AD 2021-20-21 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
Applicability*9
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.
Compliance
Comply with this AD within the compliance times specified, unless already done.
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.
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.
Affected ADs
This AD replaces AD 2018-16-10, Amendment 39-19350 (83 FR 43742, August 28, 2018) (AD 2018-16-10).
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