Airworthiness Directive · Amendment 39-14404 · Rolls-Royce plc RB211 Trent 800 Series Turbofan Engines
Rolls-Royce plc RB211 Trent 800 Series Turbofan Engines
This AD applies to Rolls-Royce plc (RR) models RB211 Trent 875-17, Trent 877-17, Trent 884-17, Trent 884B-17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan engines, with low pressure (LP) compressor fan blades, part number FW18548 installed. These engines are installed on, but not limited to, Boeing 777 series airplanes.
The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) models RB211 Trent 875-17, Trent 877-17, Trent 884-17, Trent 884B-17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan engines with low pressure (LP) compressor fan blades, part number (P/N) FW18548 installed. That AD currently requires LP compressor fan blade replacement with new or previously reworked blades, or rework of the existing LP compressor fan blades. This ad requires the same actions but at reduced compliance times for certain airplane and engine rating combinations and certain maximum gross weight limits. This AD results from a number of new production LP compressor fan blades found with surfaces formed outside of design intent. We are issuing this AD to prevent possible multiple uncontained LP compressor fan blade failure, due to cracking in the blade root caused by increased stresses in the shear key slots.
You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.
Replace LP compressor fan blades with new or previously reworked LP compressor blades before accumulating the specified cycles-since-new (CSN) in the following Table 1, or rework the existing blades as specified in paragraph (g) of this AD.
| Boeing 777 Series: | Airplane maximum gross weight (times 1,000 pounds) | RB211 Trent Engine Model | Replace or rework LP compressor fan blades before accumulating: |
|---|---|---|---|
| -300 | 660, 632.5 | -884, -892, -884B | 2,400 CSN. |
| -200 | 656 | -892, -895 | 2,400 CSN. |
| -200 | 648 | -892, -892B | 3,200 CSN. |
| -200 | 632.5 | -892B | 3,200 CSN. |
| -200 | 632.5 | -892 | 4,100 CSN. |
| -200 | 555 | -884 | 4,100 CSN. |
| -200 | 545 | -877 | 4,100 CSN. |
| -200 | 535 | -875 | 4,100 CSN. |
| -200 | 506 | -875 | 4,100 CSN. |
(g) Rework LP compressor fan blades at or before accumulating the specified CSN in Table 1 of this AD. Follow paragraphs 3.B.(1) through 3.B.(22) of Accomplishment Instructions of RR service bulletin (SB) No. RB.211-72-E044, Revision 2, dated October 8, 2004, to do the blade rework.
(h) For engines moved between configurations, calculate the cycles remaining using either of the following:
(1) Subtract the total CSN from the most limiting configuration's limit from Table 1 of this AD; or
(2) Calculate the cycles remaining using the following equation:
Where:
Xr = Cycles remaining in current configuration.
Lc = Cyclic limit of current configuration from Table 1 of this AD.
Xn = Cycles accumulated in configuration n.
Ln = Cyclic limit in configuration n from Table 1 of this AD.
(i) Information on the source life of the cycle limits in Table 1 of this AD can be found in RR Alert SB No. RB.211-72-AE055, Revision 3, dated May 28, 2004.
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.
