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2009-14-08: High-pressure compressor rotor (HPCR) stages 11-14 spool/ shafts

FAA order 2009-14-08 is an airworthiness directive in force since August 5, 2009. The FAA's subject line: High-pressure compressor rotor (HPCR) stages 11-14 spool/ shafts. It names the General Electric CF6-80C2B5F engine: about 4 aircraft on the U.S. register today, though an order usually covers particular versions or serial numbers rather than every one. System: engine.

What it applies to as the FAA lists it

Kind of product
Engine
Makes
General Electric Company
Models
CF6-80C2B5F
Engine series
General Electric CF6-80C2B5F 4 aircraft

Dates and paperwork

In force since
August 5, 2009
Published
July 1, 2009 (signed June 25, 2009)
Docket
FAA-2009-0121
Status
Current
The FAA's document
Read the order on the FAA's site

The FAA's summary their words, unchanged

The FAA is adopting a new airworthiness directive (AD) for GE CF6-80C2B5F turbofan engines. This AD requires removing certain part number (P/N) high-pressure compressor rotor (HPCR) stages 11-14 spool/ shafts before they exceed a new, reduced life limit. This AD results from an internal GE audit that compared the life limited parts certification documentation to the airworthiness limitations section (ALS) of the instructions for continuing airworthiness (ICA). We are issuing this AD to prevent HPCR stages 11-14 spool/shaft fatigue cracks caused by exceeding the life limit, which could result in a possible uncontained failure of the HPCR spool/shaft and damage to the airplane.

The order itself the regulatory text, as published

Show the full text (2,276 characters)
2009-14-08 General Electric Company: Amendment 39-15958. Docket No. FAA-2009-0121; Directorate Identifier 2008-NE-36-AD. Effective Date (a) This airworthiness directive (AD) becomes effective August 5, 2009. Affected ADs (b) None. Applicability (c) This AD applies to General Electric Company (GE) CF6-80C2B5F turbofan engines with a high-pressure compressor rotor (HPCR) stages 11-14 spool/shaft, part number (P/N) 1703M74G03, installed. These engines are installed on, but not limited to, Boeing 747 series airplanes. Unsafe Condition (d) This AD results from an internal GE audit that compared the life limited parts certification documentation to the airworthiness limitations section (ALS) of the instructions for continuing airworthiness (ICA). We are issuing this AD to prevent HPCR stages 11-14 spool/shaft fatigue cracks caused by exceeding the life limit, which could result in a possible uncontained failure of the HPCR spool/shaft and damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. New Reduced Life Limit for the HPCR Stages 11-14 Spool/Shaft (f) Remove any CF6-80C2B5F turbofan engine that has an HPCR stages 11-14 spool/shaft, P/N 1703M74G03, before the spool/shaft meets or exceeds the new, reduced life cycle limit of 19,500 cycles. Installation Prohibition (g) After the effective date of this AD, do not install any CF6- 80C2B5F turbofan engine that has an HPCR stages 11-14 spool/shaft, P/N 1703M74G03, that meets or exceeds 19,500 cycles. Alternative Methods of Compliance (h) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Special Flight Permits (i) Under 14 CFR part 39.23, we are prohibiting special flight permits for this AD. Related Information (j) Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Part, Burlington, MA 01803; e-mail: [email protected]; telephone (781) 238-7754; fax (781) 238-7199. Material Incorporated by Reference (k) None.

Source: FAA Dynamic Regulatory System, airworthiness directives. The FAA's document is the authority; the register counts are this site's, from the FAA register of October 30, 2026. Connections as data: /graph/directive/2009-14-08.json · aircraft systems.