Airworthiness Directive · Amendment 39-17603 · Rolls-Royce plc Turbofan Engines
Rolls-Royce plc Turbofan Engines
This AD applies to the following Rolls-Royce plc (RR) model turbofan engines that have a high-pressure (HP) compressor stage 1 to 4 rotor disc installed, with a part number (P/N) listed in Table 1 to paragraph (c) of this AD:
(1) RB211 Trent 553-61, 553A2-61, 556-61, 556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61; and
(2) RB211 Trent 768-60, 772-60, and 772B-60; and
(3) RB211-Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17; and
(4) RB211-524G2-T-19, -524G3-T-19, -524H-T-36, and -524H2-T-19.
| Engine model | HP Compressor stage 1 to 4 rotor disc P/N |
|---|---|
| 1. RB211 Trent 553-61, 553A2-61, 556-61, 556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61 | FK30524 or FW88340. |
| 2. RB211 Trent 768-60, 772-60, and 772B-60 | FK22745, FK24031, FK23313, FK25502, FK26185, FK32129, FW20195, FW20196, FW20197, FW20638, FW23711, FW88695, FW88696, FW88697, FW88698, FW88699, FW88700, FW88701, FW88702, or FW88703. |
| 3. RB211 Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17 | FK24009, FK26167, FK32580, FW11590, FW61622, FW88723, FW88724, or FW88725. |
| 4. RB211-524G2-T-19, -524G3-T-19, -524H-T-36, and -524H2-T-19 | FK25502, FW20195, FW23711, FW88695, FW88696, or FW88697. |
We are superseding airworthiness directive (AD) AD 2012-04-13, for all Rolls-Royce plc (RR) model RB211 Trent 553-61, 553A2-61, 556- 61, 556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61; and RB211 Trent 768-60, 772-60, and 772B-60; and RB211-Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17; and RB211-524G2-T-19, -524G3-T- 19, -524H-T-36, and -524H2-T-19 turbofan engines that have a high- pressure (HP) compressor stage 1 to 4 rotor disc installed, with a certain part number (P/N) installed. AD 2012-04-13 required repetitive inspections of the axial dovetail slots and follow-on corrective action depending on findings. This new AD expands the population of affected parts. This AD also changes, for the purposes of this AD, the definition of "engine shop visit." This AD was prompted by reports of additional affected HP compressor rotor discs that require the same action. We are issuing this AD to detect cracks in the HP compressor stage 1 and 2 disc posts, which could result in failure of the disc post and HP compressor blades, damage to the engine, and damage to the airplane.
(1) Clean and perform a fluorescent-penetrant inspection of the HP compressor stage 1 to 4 rotor disc at the first shop visit after accumulating 1,000 cycles since new (CSN) on the stage 1 to 4 rotor disc or at the next shop visit after the effective date of this AD, whichever occurs later.
(2) Use paragraphs 3.A. through 3.E.(11) of the Accomplishment Instructions of RR Alert Non-Modification Service Bulletin (NMSB) No. RB.211-72-AF964, Revision 3, dated January 11, 2013, to do the cleaning and inspection.
(3) Thereafter, at every engine shop visit, clean and inspect as required by paragraph (f)(2) of this AD.
(4) If on the effective date of this AD, an engine with an affected part has 1,000 CSN or more, and is in the shop, clean and inspect as required by paragraph (f)(2) of this AD before returning the engine to service.
(5) If cracks or anomalies are found during the inspection required by paragraph (f)(2) of this AD, accomplish the applicable corrective actions before returning the engine to service.
For the purpose of this AD, an “engine shop visit” is whenever the HP compressor rotor is accessible and the compressor blades have been removed.
If you performed cleanings and inspections before the effective date of this AD using RR NMSB No. RB.211-72-AF964, Revision 1, dated June 6, 2008, or Revision 2, dated June 8, 2011, then you met the requirements of paragraph (f) of 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.
