Airworthiness directives › 2016-25-10
AD 2016-25-10 Airworthiness Directives; Rolls-Royce plc Turbofan Engines
Applicability*9
This AD applies to Rolls-Royce plc (RR) RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 turbofan engines that have not incorporated RR modification 72-J195, in production, or RR Service Bulletin RB.211-72-J195, dated February 26, 2016, in service.
Compliance
The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: ANE-AD-AMOC@faa.gov.
Required actions
(1) For more information about this AD, contact Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, 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 2016-0078, dated April 20, 2016 (corrected April 27, 2016), 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-2016-6744.
Unsafe condition
Comply with this AD within the compliance times specified, unless already done. (1) Before the HPC stage 1-4 rotor disks shaft cyclic life exceeds 5,000 duty cycles since new, or 5,000 duty cycles since last HPC stage 1-4 rotor disks shaft piece-part inspection, whichever occurs later, do the following: (i) Perform fluorescent penetrant and visual inspections of the HPC stage 1-4 rotor disks shaft forward stage 3-4 seal fin and aft face of the stage 3 disk rim for cracks and flame erosion. Any findings of cracks or flame erosion constitute a failure of the HPC stage 1-4 rotor disks shaft. (ii) Machine the HPC stage 3 inner shroud to the dimensions shown in Figure 1 of RR Service Bulletin (SB) RB.211-72-J195, dated February 26, 2016. (2) If the HPC stage 1-4 rotor disks shaft fails the inspections required by paragraph (e)(1)(i) of this AD, replace with a part eligible for installation before further flight.
Affected ADs
None.
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