Airworthiness Directive · Amendment 39-17004 · Rolls-Royce plc Turbofan Engines
Rolls-Royce plc Turbofan Engines
Superseded. A later AD replaced this one: AD 2012-18-07. Comply with the one in force.
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.
We are superseding an existing airworthiness directive (AD) for all 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 AD currently requires initial and repetitive ultrasonic inspections (UIs) of certain low-pressure (LP) compressor blades identified by serial number (S/N). This AD requires the same actions but expands the population of blades. This AD was prompted by RR concluding that additional blades affected must be inspected. We are issuing this AD to prevent LP compressor blades from failing due to blade root cracks, which could lead to uncontained engine failure and damage to the airplane.
Unless already done, do the following actions.
(1) Perform an initial ultrasonic inspection (UI) of the affected LP compressor blades identified by S/N in Appendices 3A through 3G of RR Alert Service Bulletin (ASB) No. RB.211-72-AG244, Revision 4, dated December 22, 2011. Use Table 1 of this AD to determine your initial inspection threshold.
| Appendix number of RR ASB No. RB.211-72-AG244, revision 4, that identifies affected LP compressor blades by S/N | Initial inspection threshold |
|---|---|
| 3A and 3B | Within 70 flight cycles after the effective date of this AD. |
| 3C | Within 10 months after the effective date of this AD. |
| 3D | Within 22 months after the effective date of this AD. |
| 3E | Within 34 months after the effective date of this AD. |
| 3F | Within 46 months after the effective date of this AD. |
| 3G | Within 58 months after the effective date of this AD. |
(2) Thereafter, perform repetitive UIs of the affected LP compressor blades within every 100 flight cycles.
(3) Use paragraphs 3.A.(1) through 3.A.(2) of Accomplishment Instructions of RR ASB No. RB.211-72-AG244, Revision 4, dated December 22, 2011, and paragraphs 1 through 3.B. of Appendix 1 of that ASB, or paragraphs 3.B.(1) through 3.B.(3) of Accomplishment Instructions of RR ASB No. RB.211-72-AG244, Revision 4, dated December 22, 2011, and paragraphs 1 through 3.C. of Appendix 2 of that ASB, to perform the UIs.
(4) Do not return to service any engine with blades that failed the inspection required by this AD.
(5) For blades that are removed from the engine and pass inspection, re-apply dry film lubricant, and install all blades in their original position.
(6) After the effective date of this AD, do not install any affected LP compressor blade unless it has passed the initial and repetitive UIs required by this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Engines
