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Airworthiness directives › 2013-26-10

AD 2013-26-10 Airworthiness Directives; Rolls-Royce plc Turbofan Engines

Superseded. This directive was replaced by AD 2023-21-03. Work to the current one.
2014-01-23
2014-01-08
39-17719
FAA-2013-1004
Engine
2023-21-03

Applicability*9

This AD applies to all Rolls-Royce plc (RR) RB211-524G2-19, RB211-524G3-19, RB211-524H-36, and RB211-524H2-19 turbofan engines with high-pressure (HP) compressor rotor stage 1 and stage 2 discs, part number LK70608, LK76030, LK86621, UL19877, UL19878, UL19879, or UL24023, installed.

Compliance

The Manager, Engine Certification Office, FAA, may approve AMOCs to this AD. Use the procedures found in 14 CFR 39.19 to make your request.

Required actions

(1) For more information about this AD, contact Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7754; fax: 781-238-7199; email: robert.green@faa.gov. (2) Refer to MCAI European Aviation Safety Agency AD 2013-0246, dated October 10, 2013, for more information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-2013-1004.

Unsafe condition

Comply with this AD within the compliance times specified, unless already done. (1) Within 30 days after the effective date of this AD, reduce the cyclic life limit for the affected HP compressor rotor stage 1 and stage 2 discs to 7,390 flight cycles (FC). (2) After the effective date of this AD, remove each affected HP compressor rotor stage 1 and stage 2 disc from service before the part exceeds 7,390 FC. (3) After the effective date of this AD, do not return to service any engine that has an HP compressor rotor stage 1 and stage 2 disc installed, if the disc has more than 7,390 FC.

Affected ADs

None.

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