Airworthiness directives › 2012-04-01
AD 2012-04-01 Airworthiness Directives; Rolls-Royce plc (RR) RB211-Trent 800 Series Turbofan Engines
Applicability*9
This AD applies to Rolls-Royce plc (RR) RB211-Trent 895-17, 892-17, 892B-17, 884-17, 884B-17, 877-17, and 875-17 turbofan engines.
Compliance
After the effective date of this AD, do not install any IP turbine rotor discs, P/N FK33083, into any engine.
Required actions
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.
Unsafe condition
Compliance is required within 30 days after the effective date of this AD, unless already done. (1) After the effective date of this AD, remove from service the parts listed in Table 1 of this AD before exceeding the new life limit indicated: Table 1—Reduced Part Lives Part nomenclature Part No. (P/N) Life in standard duty cycles Life in cycles using the HEAVY profile (i) Intermediate-pressure (IP) Compressor Rotor Shaft FK24100 8,140 8,140 (ii) IP Compressor Rotor Shaft FK24496 8,860 8,180 (iii) High-pressure (HP) Compressor Stage 1 to 4 Rotor Discs Shaft FK24009 4,560 4,460 (iv) HP Compressor Stage 1 to 4 Rotor Discs Shaft FK26167 6,340 6,000 (v) HP Compressor Stage 1 to 4 Rotor Discs Shaft FK32580 8,550 6,850 (vi) HP Compressor Stage 1 to 4 Rotor Discs Shaft FW11590 8,550 6,850 (vii) HP Compressor Stage 1 to 4 Rotor Discs Shaft FW61622 8,550 6,850 (viii) HP Compressor Stage 5 and 6 Discs and Cone FK25230 5,000 5,000 (ix) HP Compressor Stage 5 and 6 Discs and Cone FK27899 5,000 5,000 (x) IP Turbine Rotor Disc FK21117 11,610 10,400 (xi) IP Turbine Rotor Disc FK33083 0 0
Affected ADs
This AD supersedes AD 2003-16-18, Amendment 39-13271 (68 FR 49344, August 18, 2003).
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