2003-12-15: LPC fan blade roots

2003-12-15 Rolls-Royce plc: Amendment 39-13200. Docket No. 2000-NE- 13-AD. Applicability: This airworthiness directive (AD) is applicable to Rolls-Royce (RR) plc RB211-535E4-37, RB211-535E4-B-37, and RB211- 535E4-B-75 series turbofan engines with low pressure compressor (LPC) fan blades with the part numbers (P/Ns) listed in Table 1 of this AD. These engines are installed on, but not limited to Boeing 757 and Tupolev Tu204 series airplanes. Table 1 follows: Table 1.--Applicable LPC Fan Blade P/Ns UL16135 UL16171 UL16182 UL19643 UL20044 UL20132 UL20616 UL21345 UL22286 UL23122 UL24525 UL24528 UL24530 UL24532 UL24534 UL27992 UL28601 UL28602 UL29511 UL29556 UL30817 UL30819 UL30933 UL30935 UL33707 UL33709 UL36992 UL37090 UL37272 UL37274 UL37276 UL37278 UL38029 UL38032 Note 1: This 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 (g) 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. Compliance: Compliance with this AD is required as indicated, unless already done. To detect cracks in LPC fan blade roots, which if not detected, could lead to uncontained multiple fan blade failure, and damage to the airplane, do the following: (a) If you have a full set of fan blades, modified using RR service bulletin RB.211-72-C946, Revision 2, dated September 26, 2002, that can be identified by a blue triangle etched on the blade airfoil suction surface close to the leading edge tip of each blade, no further action is required. (b) On RB211-535E4 engines, operated to Flight Profile A, ultrasonically inspect, and if required, relubricate using the following Table 2: Table 2.--RB211-535E4 Flight Profile A Engine location Initial inspection within (CSN) Type action In accordance with Repeat inspection within (CSN) (1) On-wing 17,350 (i) Root Probe, inspect and relubricate, OR (ii) Wave Probe RB.211-72-C879 Revision 3, 3.A.(1) through 3.A.(7), dated October 9, 2002. RB.211-72-C879 Revision 3, 3.B.(1) through 3.B.(7), dated October 9, 2002. 1,400. 1,150. (2) In Shop 17,350 Root Probe, inspect and relubricate RB.211-72-C879 Revision 3, 3.C.(1) through 3.C.(4), dated October 9, 2002. 1,400. (c) On RB211-535E4 engines, operated to Flight Profile B, ultrasonically inspect, and if required, relubricate using the following Table 3: Table 3.--RB211-535E4 Flight Profile B Engine location Initial inspection within (CSN) Type action In accordance with Repeat inspection within (CSN) (1) On-wing 12,350 (i) Root Probe, inspect and relubricate, OR (ii) Wave Probe RB.211-72-C879 Revision 3, 3.A.(1) through 3.A.(7), dated October 9, 2002. RB.211-72-C879 Revision 3, 3.B.(1) through 3.B.(7), dated October 9, 2002. 850. 700. (2) In Shop 12,350 Root Probe, inspect and relubricate RB.211-72-C879 Revision 3, 3.C.(1) through 3.C.(4), dated October 9, 2002. 850. (d) On RB211-535E4 engines, operated to combined Flight Profile A and B, ultrasonically inspect, and if required, relubricate using the following Table 4: Table 4.--RB211-535E4 Flight Profile A and B Engine location Initial inspection within (CSN) Type action In accordance with Repeat inspection within (CSN) (1) On-wing 65% hard life (To calculate, see Compliance Section 1.C.(4)). (i) Root Probe,inspect and relubricate, OR. (ii) Wave Probe RB.211-72-C879 Revision 3, 3.A.(1) through 3.A.(7), dated October 9, 2002. RB.211-72-C879 Revision 3, 3.B.(1) through 3.B.(7), dated October 9, 2002. As current flight profile. As current flight profile. (2) In Shop 65% hard life (To calculate, see Compliance Section 1.C.(4)). Root Probe, inspect and relubricate. RB.211-72-C879 Revision 3, 3.C.(1) through 3.C.(4), dated October 9, 2002 As current flight profile. Note 2: Fan blades that have been operated within RB211-535E4 Flight Profile A and B will have final life as defined in the Time Limits Manual. See References Section 1.G.(3), of MSB RB.211-72- C879, Revision 3, dated October 9, 2002. (e) On RB211-535E4-B engines, ultrasonically inspect, and if required, relubricate using the following Table 5: Table 5.--RB211-535E4-B Engine location Initial inspection within (CSN) Type action In accordance with Repeat inspection within (CSN)(1) On-wing. 17,000. (i) Root Probe, inspect and relubricate, OR (ii) Wave Probe. RB.211-72-C879 Revision 3, 3.A.(1) through 3.A.(7), dated October 9, 2002. RB.211-72-C879 Revision 3,3.B.(1) through 3.B.(7), dated October 9, 2002.. 1,200. 1,000. (2) In Shop. 17,000. Root Probe, inspect and relubricate. RB.211-72-C879 Revision 3,3.C.(1) through 3.C.(4), dated October 9, 2002. 1,200. Optional Terminating Action (f) Application of Metco 58 blade root coating using RR SB RB.211-72-C946, Revision 2, dated September 26, 2002, constitutes terminating action to the repetitive inspection requirements specified in paragraphs (b), (c), (d), and (e) of this AD. Alternative Methods of Compliance (g) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office (ECO). Operators must submit their request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, ECO. Note 3: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the ECO. Special Flight Permits (h) Special flight permits may be issued in accordance with 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be done. Documents That Have Been Incorporated By Reference (i) The inspections must be done in accordance with Rolls-Royce plc mandatory service bulletin RB.211-72-C879, Revision 3, dated October 9, 2002. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone: 011-44-1332-242-424; fax: 011-44-1332-249-936.Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. Note 4: The subject of this AD is addressed in CAA airworthiness directive AD 002-01-2000, dated October 9, 2002. Effective Date (j) This amendment becomes effective on July 30, 2003.