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Federal Register / Vol. 86, No. 210 / Wednesday, November 3, 2021 / Rules and Regulations 2 GEAC H85200 model turboprop engines build configuration BC04 with Avia Propeller AV725 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.

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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
20181610, 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 PS2, with beta switch, P/N PS2A, using paragraphs 1.6 and 1.7 of GEAC Service Bulletin SB SBH807600000036 03, formatted as service bulletin identifier revision number, dated April 12, 2019
GEAC SB SBH807600000036 03 or paragraphs 1.6 and 1.7 of GEAC SBH8076
00000036 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
M60176.3, using paragraph 1.6 of GEAC
Alert Service Bulletin ASB ASBH8076
0000004801/ASBH857600000015
01 single document, formatted as service bulletin identifier revision number, dated April 12, 2019 GEAC ASB ASBH807600
00004801/ASBH857600000015 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 M60176.3, with engine pushpull control P/N M60176.4 or P/N M601
76.5, as applicable to the engine model, using Appendix 1 of GEAC ASB ASBH807600
00004704/ASBH85760000001804
single document, formatted as service bulletin identifier revision number, dated May 8, 2020 GEAC ASB ASBH807600
00004704/ASBH85760000001804.
4 For engines modified as required by paragraph g3 of this AD: Within 100 FHs or during a subsequent Type 2 inspection, whichever occurs first after the engine modification required by paragraph g3 of this AD, and thereafter, at intervals not to exceed 100 FHs from the previous inspection, inspect the engine push-pull
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control, P/N M60176.4 or P/N M60176.5, using the Accomplishment Instructions, paragraph 2.1.2, of GEAC ASBH807600
00004704/ASBH85760000001804.
Note 1 to paragraph g4: 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 g3
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 M60176.4 or P/N M60176.5, as applicable, using the instructions in Table 601 Sheet 14 of Section 720000, dated December 14, 2012, of the GE Aviation Business & General AviationTurboprops 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 g1 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
SBH807600000036 03 or paragraph 1.6.1 of GEAC ASB ASBH80760000
004801/ASBH857600000015 01, as applicable.
7 If, during any inspection required by paragraph g4 of this AD, any deficiencies are detected, before next flight, perform the actions in paragraph 2.1.2 of GEAC ASB
ASBH80760000004704/ASBH85
760000001804.
8 If, during the inspection as required by paragraph g5 of this AD, any deficiencies are detected, before next flight, correct those deficiencies using the instructions in Table 601 Sheet 14, Section 720000, 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 PS2, on any engine, after modification of the engine as required by paragraph g1 of this AD.
2 For Group 2, Group 3, Group 4, and Group 5 engines: Do not install a beta switch, P/N PS2, on any engine.
3 For Group 1, Group 2, and Group 3
engines: Do not install an engine push-pull control, P/N M60176.3, on any engine after modification of the engine as required by paragraph g3 of this AD.
i Terminating Action Accomplishing the inspection of the engine push-pull control, P/N M60176.4 or P/N M60176.5, as required by paragraph g4 of this AD, without finding any deficiencies during six consecutive inspections, constitutes a terminating action for the repetitive inspections required by paragraph g4 of this AD for that engine.

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j No Communication or Reporting Requirements The instructions to contact the manufacturer for further instructions in paragraph 2.1, of GEAC ASB ASBH8076
0000004704/ASBH85760000
001804, are not required by this AD.
k Definitions 1 Group 1 engines are GEAC H80200
model turboprop engines that have an engine push-pull control, P/N M60176.3, and a beta switch, P/N PS2, installed.
2 Group 2 engines are GEAC H80200
model turboprop engines that have an engine push-pull control, P/N M60176.3, but no beta switch, P/N PS2, installed.
3 Group 3 engines are GEAC H85200
model turboprop engines build configuration BC04 that have an engine push-pull control, P/N M60176.3, installed.
4 Group 4 engines are GEAC H80200
model turboprop engines that have an engine push-pull control, P/N M60176.5, installed.
5 Group 5 engines are GEAC H85200
model turboprop engines build configuration BC04 that have an engine push-pull control, P/N M60176.4, 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 g2 of this AD if you performed the actions before the effective date of this AD using GEAC ASB
H80760000004800/ASBH857600
00001500 single document, dated April 12, 2019.
2 You may take credit for the installation of the engine push-pull control required by paragraph g3 of this AD and the initial inspection of the engine push-pull control required by paragraph g4 of this AD, if you performed these actions before the effective date of this AD using GEAC ASB ASBH80
760000004703/ASBH85760000
001803 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 n1 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
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