Airworthiness Directive · Amendment 39-21759 · Engine controls
GE Aviation Czech s.r.o. (Type Certificate Previously Held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.) Turboprop Engines
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.
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.
(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.
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.
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.
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.
(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.
