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2009-21-09: High-pressure (HP) compressor rotor rear stage 5 and 6 discs and cone shafts

FAA order 2009-21-09 is an airworthiness directive in force since November 20, 2009. The FAA's subject line: High-pressure (HP) compressor rotor rear stage 5 and 6 discs and cone shafts. It names the Rolls-Royce RB-211 series engine: about 182 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: Rolls-Royce plc
Models: RB211-Trent 892B-17, RB211-Trent 895-17, RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 892-17
Engine series: Rolls-Royce RB-211 series 182 aircraft

Dates and paperwork

In force since: November 20, 2009
Published: October 16, 2009 (signed October 8, 2009)
Docket: FAA-2009-1369
Replaces: 2003-15-06
Status: Current
The FAA's document: Read the order on the FAA's site

The FAA's summary their words, unchanged

The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc RB211 Trent 875-17, Trent 877-17, Trent 884- 17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan engines with high-pressure (HP) compressor rotor rear stage 5 and 6 discs and cone shafts, part numbers (P/Ns) FK25230 and FK27899 installed. That AD currently requires removal from service of these HP compressor rotor rear stage 5 and 6 discs and cone shafts before reaching newly reduced life limits. This AD requires removing these parts at new reduced cycle limits. This AD results from Rolls-Royce plc reducing the lives of these parts and changing the life calculating method to use "Standard Duty Cycles'' with "Multiple Flight Profile Monitoring'' and "Flight Cycles'' with "Heavy Flight Profile Monitoring''. We are issuing this AD to prevent stage 5 and 6 disc crack initiation and propagation that might lead to uncontained disc failure and damage to the airplane.

The order itself the regulatory text, as published

Show the full text (3,066 characters)

2009-21-09 Rolls-Royce plc: Amendment 39-16048. Docket No. FAA-2009- 1369; Directorate Identifier 2003-NE-03-AD. 

Effective Date 

	(a) This airworthiness directive (AD) becomes effective November 20, 2009. 

Affected ADs 

	(b) This AD supersedes AD 2003-15-06, Amendment 39-13249. 

Applicability 

	(c) This AD applies to Rolls-Royce plc RB211 Trent 875-17, Trent 877-17, Trent 884-17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan engines with high-pressure (HP) compressor rotor rear stage 5 and 6 discs and cone shafts, part numbers FK25230 and FK27899 installed. These engines are installed on, but not limited to, Boeing 777 series airplanes. 

Unsafe Condition 

	(d) This AD results from Rolls-Royce plc reducing the lives of these parts and changing the life calculating method to use "Standard Duty Cycles'' with "Multiple Flight Profile Monitoring'', and "Flight Cycles'' with "Heavy Flight Profile Monitoring''. We are issuing this AD to prevent stage 5 and6 disc crack initiation and propagation that might lead to uncontained disc failure 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. 

	(f) For operators using "Multiple Flight Profile Monitoring'' (Flight Profiles "A'' through "F''), remove HP compressor rotor rear stage 5 and 6 discs and cone shafts from service at or before accumulating 5,000 "Standard Duty Cycles''. Guidance on "Multiple Flight Profile Monitoring'' can be found in the Aircraft Maintenance Manual, Chapter 70-01-10. 

	(g) For operators using "Heavy Flight Profile Monitoring'', remove HP compressor rotor rear stage 5 and 6 discs and cone shafts from service at or before accumulating 5,000 "Flight Cycles''. Guidance on "Heavy Flight Profile Monitoring'' can be found in the Aircraft Maintenance Manual, Chapter 70-01-10. 

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. 

Related Information 

	(i) Contact James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803, e-mail [email protected]; telephone (781) 238-7176; fax (781) 238- 7199, for more information about this AD. 

	(j) European Aviation Safety Agency AD 2007-0004, dated January 8, 2007, also addresses the subject of this AD. 

	(k) Rolls-Royce plc Alert Service Bulletin No. RB.211-72-AE082, Revision 7, dated June 18, 2008, pertains to the subject of this AD. Contact Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, UK, telephone 44 (0) 1332 242424; fax 44 (0) 1332 249936, for a copy of this service information. 

	(l) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207, for a copy of the Aircraft Maintenance Manual referenced in this AD. 

Material Incorporated by Reference 

	(m) 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 November 3, 2026. Connections as data: /graph/directive/2009-21-09.json · aircraft systems.