AD 95-10-11
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | General Electric Company | CF6-80C2A1 | Airworthiness Directives; General Electric Company CF6 Series Turbofan Engines |
| engine | General Electric Company | CF6-80C2A2 | Airworthiness Directives; General Electric Company CF6 Series Turbofan Engines |
| engine | General Electric Company | CF6-80C2A3 | Airworthiness Directives; General Electric Company CF6 Series Turbofan Engines |
| engine | General Electric Company | CF6-80C2A5 | Airworthiness Directives; General Electric Company CF6 Series Turbofan Engines |
| engine | General Electric Company | CF6-80C2A5F | Airworthiness Directives; General Electric Company CF6 Series Turbofan Engines |
| engine | General Electric Company | CF6-80C2A8 | Airworthiness Directives; General Electric Company CF6 Series Turbofan Engines |
| engine | General Electric Company | CF6-80C2B1 | Airworthiness Directives; General Electric Company CF6 Series Turbofan Engines |
| engine | General Electric Company | CF6-80C2B1F | Airworthiness Directives; General Electric Company CF6 Series Turbofan Engines |
| engine | General Electric Company | CF6-80C2B1F1 | Airworthiness Directives; General Electric Company CF6 Series Turbofan Engines |
| engine | General Electric Company | CF6-80C2B1F2 | Airworthiness Directives; General Electric Company CF6 Series Turbofan Engines |
Unsafe Condition
The CDU brake shaft wear due to low material hardness from an omitted heat treat step could result in loss of brake holding feature, allowing uncommanded movement of the fan reverser translating cowl towards the deploy position in flight.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Perform initial and repetitive brake holding torque checks of the CDU, visual inspections of the translating cowl inner bondment seal, functional checks of the auto re-stow system, and replace certain CDUs as a terminating action.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Prior to accumulating 250 cycles in service (CIS) or 30 days after the effective date of this AD, whichever occurs earlier.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
General Electric Company CF6-80C2 series turbofan engines installed on Airbus A300/A310, Boeing 747/767, and McDonnell Douglas MD-11 series aircraft.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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