Airworthiness directives › 2012-14-09
AD 2012-14-09 Airworthiness Directives; Pratt & Whitney (P&W) Division Turbofan Engines
Applicability*9
This AD applies to the following Pratt & Whitney Division turbofan engines: (1) PW4000-94″ engine models PW4050, PW4052, PW4056, PW4152, PW4156, PW4650, PW4060, PW4060A, PW4060C, PW4062, PW4062A, PW4156A, PW4158, PW4160, PW4460, and PW4462 including models with any dash number suffix. (2) PW4000-100″ engine models PW4164, PW4164C, PW4164C/B, PW4168, PW4168A, PW4164-1D, PW4164C-1D, PW4164C/B-1D, PW4168-1D, PW4168A-1D, and PW4170.
Compliance
After the effective date of this AD, do not install or reinstall into any engine any LPT 4th stage vanes with a P/N listed in Table 1 to paragraph (e) of this AD that are at piece-part exposure and have had more than one strip and recoat repair.
Required actions
(1) For the purpose of this AD, an HPT or LPT overhaul occurs when all disks in the rotor are removed from the engine and the blades are removed. (2) For the purpose of this AD, piece-part exposure means that the part is removed from the engine and completely disassembled.
Unsafe condition
Comply with this AD within the compliance times specified, unless already done. (1) At the next LPT overhaul, do the following: (i) Remove LPT 4th stage vanes that have a P/N listed in Table 1 to paragraph (e) of this AD from service if more than one strip and recoat repair has been performed. Table 1 to Paragraph (e) —Affected LPT 4th Stage Vane P/Ns 50N174 50N674-01 51N174-001 51N374-001 52N574-01 50N474-01 50N774-01 51N174-002 51N674-01 52N674-01 50N474-001 50N774-001 51N174-003 52N274-01 51N774-01 50N574-01 51N174-01 51N374-01 52N474-01 52N774-01 (ii) Re-assemble the 3rd stage LPT rotor blades by alternating heavy blades next to light blades and balancing blades of similar weights 180 degrees across the rotor. (iii) Dimensionally examine index 13 through index 34 of the LPT 3rd stage vane cluster assembly. Use Table 2 to paragraph (e) of this AD and Figure 1, Figure 2, and Figure 3 to paragraph (e) of this AD to determine whether the vane is eligible for installation. Table 2 to Paragraph (e) —Determination of Vane Eligibility Inspect: Eligible for installation limits: 13 1.820-1.830 inches (46.23-46.48 mm). 14 1.920-1.930 inches (48.77-49.02 mm). 15 3.200 inches (81.280 mm) Basic. 16 0.900 inch (22.860 mm) Basic. 17 0.365 inch (9.271 mm) Basic. 18 0.350 inch (8.890 mm) Basic. 19 0.160 inch (4.064 mm) Basic. 20 0.772 inch (19.609 mm) Basic. 21 72° Basic. 22 22.382 inch (568.503 mm) Radius—Origin on Plane S Basic. 23 21.052 inch (534.721 mm) Radius—Origin on Plane S, concentric with Index 8 Basic. 24 Angle from Plane S to Plane SL 3°4′37″ Basic. 25 Angle from Plane S to Plane SM 6°9′14″ Basic. 26 90° Basic for typical airfoil section. 27: Distance from rear foot outer diameter surface to airfoil section along Planes S, SL, and SM For Section B-B: 5.241 inches (133.121 mm). For Section E-E: 3.181 inches (80.797 mm). For Section J-J: 1.935 inches (49.149 mm). 28: Airfoil chord at Section J-J (1.935 inches (49.149 mm) from rear foot outer diameter surface at Planes S, SL, and SM) 1.346 inches (34.188 mm) minimum. At Section E-E (3.181 inches (80.797 mm) from rear foot outer diameter surface at Planes S, SL, and SM) 1.314 inches (33.376 mm) minimum. At Section B-B (5.241 inches (133.121 mm) from rear foot outer diameter surface at Planes S, SL, and SM) 1.188 inches (30.175 mm) minimum. 29: Airfoil thickness at Section J-J (1.935 inches (49.149 mm) from rear foot outer diameter surface at Planes S, SL, and SM) 0.239 inch (6.071 mm) minimum. At Section E-E (3.181 inches (80.797 mm) from rear foot outer diameter surface at Planes S, SL, and SM) 0.183 inch (4.648 mm) minimum. At Section B-B (5.241 inches (133.121 mm) from rear foot outer diameter surface at Planes S, SL, and SM) 0.139 inch (3.531 mm) minimum. 30: Distance to trailing edge measurement 0.062 inch (1.575 mm). 31: Airfoil trailing edge thickness 0.030 inch (0.762 mm) minimum. 32: Dimension 0.315-0.324 inch (8.001-8.230 mm) diameter. 33: Dimension 6.785-6.795 inches (172.34-172.59 mm). 34: Dimension 0.692-0.714 inch (17.58-18.14 mm). BILLING CODE 4910-13-P ER03OC12.000 ER03OC12.001 ER03OC12.002 BILLING CODE 4910-13-C (iv) Dimensionally examine index 23 and index 24 of the vane engagement slots on the rear turbine case, where the 3rd stage vane is installed. Use Table 3 to paragraph (e) of this AD and Figure 4 to paragraph (e) of this AD to determine whether the case is eligible for installation. Table 3 to Paragraph (e) —Determination of Case Eligibility Inspect: Eligible for installation limits: 23 1.875 inch (47.625 mm) minimum. 24 0.097 inch (2.464 mm) minimum. ER03OC12.003 (v) Inspect the 44 LPT 4th stage vane cluster assemblies P/N 52N774-01 for casting identification “51N554AT 1447 2S1C1” and P/N 52N674-01 for casting identification “51N454AT 655 2S1C1.” Remove the vane cluster assembly from service if either of these casting identifications is found. (2) At the next high-pressure turbine (HPT) overhaul, re-assemble the 2nd stage HPT rotor blades by alte
Affected ADs
None.
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