Airworthiness Directive · Amendment 39-11804 · Rolls-Royce plc. RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 Turbofan Engines
Rolls-Royce plc. RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 Turbofan Engines
This AD is applicable to Rolls-Royce plc. (RR) RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan engines with fan blade part numbers (P/N's) FK22580, FK23411, FK25441, and FK25968 installed. These engines are installed on but not limited to Airbus A330-341 and A330-342 series airplanes.
Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc. (RR) RB211 Trent 768-60, Trent 772- 60, and Trent 772B-60 turbofan engines. This action requires initial and repetitive ultrasonic inspections for cracks in fan blade dovetail roots, and if necessary, replacement with serviceable parts. This amendment is prompted by reports of fan blade failures due to dovetail root cracks. The actions specified in this AD are intended to prevent possible multiple fan blade failures, which could result in an uncontained engine failure and damage to the airplane.
Compliance with this AD is required as indicated below, unless already completed.
To prevent possible multiple fan blade failures, which could result in an uncontained engine failure and damage to the airplane, do the following:
Ultrasonically inspect the dovetail roots of all fan blade P/N's FK22580, FK23411, FK25441, and FK25968 with more than 2800 cycles since new (CSN), for cracks as follows:
(1) Initially inspect the fan blade in accordance with paragraph 3.A.(1) or paragraph 3.B.(1) through paragraph 3.B.(8) of RR service bulletin (SB) No. RB.211-72-C878, revision 1, dated December 10, 1999, at the later of the following:
(i) Within 200 fan blade cycles in service (CIS) after the effective date of this AD; or
(ii) Within 200 fan blade CIS of achieving 2800 CSN.
(2) Thereafter, inspect at intervals not to exceed 340 CIS, since last inspection, in accordance with paragraph 3.A.(1) or paragraph 3.B.(1) through paragraph 3.B.(8) of RR SB No. RB.211-72-C878, revision 1, dated December 10, 1999.
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.
