EASA Regulations for General Electric CF34-8

10 airworthiness directives and regulations affecting General Electric CF34-8.

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New ADs and bulletins for General Electric CF34-8, summarized like the ones below, every Monday.

EASA AD US-2025-12-08

Jul 16, 2025

Turbine Engine - Combustion Chamber Assembly - Inspection

The Federal Aviation Administration's Airworthiness Directive 2025-12-08 addresses certain General Electric Company CF34-8 series engines, including models CF34-8C1 through CF34-8E6A1. This directive mandates inspections of the combustion chamber assembly (CCA) forward flange using fluorescent penetrant inspection (FPI) techniques to detect potential cracks and requires replacement if necessary. The AD aims to mitigate a predicted reduction in the cyclic life of the CCA forward flange to ensure continued airworthiness.

Airworthiness Directive

General Electric CF34-8

EASA AD US-2023-02-05

Mar 7, 2023

Time Limits / Maintenance Checks — Airworthiness Limitations Section — Amendment

The Federal Aviation Administration's Airworthiness Directive 2023-02-05 is a final rule addressing General Electric Company CF34-8C and CF34-8E model turbofan engines. It mandates revisions to the airworthiness limitations section of the engine manuals and operators' maintenance programs to include initial and repetitive fluorescent penetrant inspections of the combustion chamber assembly aft flange. This directive aims to mitigate a predicted reduction in the cyclic life of this critical engine component.

Airworthiness Directive

General Electric CF34-8

EASA AD US-2022-21-06

Nov 10, 2022

Engine - Low Pressure Turbine Stage 5 Discs - Removal / Replacement

The Federal Aviation Administration's Airworthiness Directive 2022-21-06 addresses certain General Electric Company CF34-8C and CF34-8E model turbofan engines. It focuses on the removal and replacement of the low-pressure turbine (LPT) stage 5 disk, part number 4117T14P02, due to a reported crack in the forward arm area. This directive aims to ensure continued airworthiness and safety of affected engines.

Airworthiness Directive

General Electric CF34-8

EASA AD US-2022-09-14

May 23, 2022

Air - Operability Bleed Valve - Inspection / Replacement

Airworthiness Directive 2022-09-14 is a final rule issued by the Federal Aviation Administration addressing General Electric Company CF34-8C and CF34-8E model turbofan engines. It mandates inspections and replacements related to the operability bleed valve (OBV) components to prevent fuel leaks and potential engine fires. This directive applies to specific OBV part numbers installed on these engine models.

Airworthiness Directive

General Electric CF34-8

EASA AD US-2022-08-06

Apr 27, 2022

Engine - Compressor Inlet Guide Vane Outer Shroud Bushing and Vane Spindle Bushing - Inspection / Replacement

The document titled "Engine - Compressor Inlet Guide Vane Outer Shroud Bushing and Vane Spindle Bushing - Inspection / Replacement" is a Federal Aviation Administration (FAA) Airworthiness Directive (AD 2022-08-06) addressing certain General Electric Company CF34-8C and CF34-8E turbofan engines. It mandates inspections and potential replacements related to corrosion issues in the variable geometry system actuator that can cause engine control problems. The AD aims to prevent engine failures and loss of thrust control on affected aircraft such as Bombardier CRJ1000 and CRJ900 models powered by these engines.

Airworthiness Directive

General Electric CF34-8
Bombardier CRJ1000
Bombardier CRJ900

EASA AD US-2021-26-19

Jan 19, 2022

Engine - High Pressure Turbine Rotor Stage 1 Disk - Replacement

The Federal Aviation Administration's Airworthiness Directive 2021-26-19 addresses certain General Electric Company CF34-8C and CF34-8E model turbofan engines. It requires the removal and replacement of the high-pressure turbine (HPT) rotor stage 1 disk, part number 4125T22P04, due to a manufacturing quality escape that could lead to disk failure. This directive applies to engines with specific serial numbers and aims to ensure continued airworthiness and safety.

Airworthiness Directive

General Electric CF34-8

EASA AD US-2021-23-51

Dec 15, 2021

[Final Rule] Engine / Air - Compressor Variable Geometry Actuator - Inspection

The Final Rule titled 'Engine / Air - Compressor Variable Geometry Actuator - Inspection' is a Federal Aviation Administration (FAA) airworthiness directive addressing certain General Electric Company CF34-8C and CF34-8E model turbofan engines. It mandates inspections of the master and slave compressor variable geometry actuators due to corrosion and seizure issues that caused an in-flight engine shutdown on a Bombardier CRJ1000 aircraft. The directive requires inspection, possible replacement of affected parts, and reporting inspection results to GE.

Airworthiness Directive

General Electric CF34-8
Bombardier CRJ1000

EASA AD US-2021-18-13

Sep 21, 2021

Engine - Combustion Outer Liner Shell - Inspection / Replacement

The Federal Aviation Administration Airworthiness Directive 2021-18-13 is a final rule addressing all General Electric Company CF34-8 model turbofan engines equipped with a specific combustion outer liner shell. This directive mandates inspections and potential replacement of the combustion outer liner shell due to failures that caused two in-flight engine shutdowns. It applies to various CF34-8C and CF34-8E engine variants and aims to mitigate unsafe conditions related to combustion liner shell cracking and collapse.

Airworthiness Directive

General Electric CF34-8

EASA AD US-2019-22-05

Dec 16, 2019

Superseded by FAA AD 2022-09-14

Airworthiness Directive 2019-22-05 is a final rule issued by the Federal Aviation Administration (FAA) that supersedes AD 2017-23-06. It applies to General Electric Company CF34-8C series turbofan engines, including models CF34-8C1, CF34-8C5, CF34-8C5A1, CF34-8C5B1, CF34-8C5A2, and CF34-8C5A3. The directive addresses safety concerns related to the operability bleed valve (OBV) to prevent engine fires and potential damage to aircraft.

Airworthiness Directive

General Electric CF34-8

EASA AD US-2018-17-14

Oct 9, 2018

Engine Exhaust - Thrust Reverser - Inspection

The Federal Aviation Administration's Airworthiness Directive 2018-17-14 addresses certain General Electric Company CF34-8E turbofan engines. It mandates a one-time inspection of the gap between the core cowl seal and the pylon seal on specific thrust reverser halves to ensure the gap width is within acceptable limits. If the gap exceeds 1 mm, the thrust reverser fire seals must be replaced to prevent potential fire hazards.

Airworthiness Directive

General Electric CF34-8