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Airworthiness directives › 2017-11-06

AD 2017-11-06 Airworthiness Directives; Pratt & Whitney Turbofan Engines

Superseded. This directive was replaced by AD 2019-05-01. Work to the current one.
2017-07-18
2017-06-13
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Engine
2019-05-01

Applicability*9

This AD applies to all Pratt & Whitney (PW) PW2037, PW2037D, PW2037M, PW2040, PW2040D, PW2043, PW2143, PW2643, and F117-PW-100 turbofan engines.

Compliance

Unless already done, comply with this AD within the compliance times specified. (1) For diffuser case, part number (P/N) 1B7461, serial numbers (S/Ns) DGGUAK1306 and DGGUAK1308, and HPT case, P/N 1B2440, S/N DKLBCS1032: (i) Within 100 flight cycles or 30 days after May 5, 2014, whichever is later, eddy current inspect the diffuser case and the HPT case M-flange. Use PW Service Bulletin (SB) No. PW2000 72-763, Revision No. 1, dated August 30, 2013, to do the inspection. (ii) Reserved. (2) For all diffuser and HPT cases, at the next piece-part opportunity and every piece-part opportunity thereafter, perform a high sensitivity fluorescent-penetrant inspection (FPI) of the entire diffuser case rear flange (M-flange) and boltholes, and the entire HPT case forward flange (M-flange) and boltholes. (3) For diffuser cases that have not incorporated PW SB PW2000-72-364 or have incorporated either PW SB PW2000-72-700 or PW2000 Series Engine Manual, Repair-28, Task 72-41-01-300-028 (M-flange replacement), perform initial and repetitive eddy current inspections (ECIs) of the M-flange of the diffuser case in accordance with paragraph (f)(4) of this AD. (4) Use, as applicable, either the Accomplishment Instructions, “For Engines Installed on the Aircraft,” paragraphs 3.(I) through 3.(J), or the Accomplishment Instructions, “For Engines Removed from the Aircraft,” paragraphs 3.(D) through 3.(E), of PW Alert Service Bulletin (ASB) No. PW2000 A72-765, Revision No. 2, dated August 12, 2016 to do the ECI as follows: (i) Perform an initial inspection within the following period, whichever occurs later: (A) Within 5,500 cycles since new or since M-flange replacement, or (B) Within 2,500 cycles since last piece-part FPI inspection, or (C) Within 1,000 cycles from the effective date of this AD. (ii) If no crack indications are found, re-inspect within 2,500 cycles since last ECI or last piece-part FPI inspection, whichever occurs later. (iii) If bolthole ID crack indications are found, measure the length and determine the re-inspect interval in accordance with: (A) Paragraphs 5.(C) through 5.(D) of PW ASB No. PW2000 A72-765, Revision No. 2, dated August 12, 2016 “For Engines Installed on the Aircraft”; or (B) Paragraphs 4.(C) through 4.(D) of PW ASB No. PW2000 A72-765, Revision No. 2, dated August 12, 2016, “For Engines Removed from the Aircraft.” (iv) Remove from service diffuser cases with bolthole ID cracks exceeding 0.170 inches.

Required actions

For the purpose of this AD, piece-part opportunity is defined as when the part is completely disassembled.

Unsafe condition

This AD was prompted by a rupture of the diffuser-to-high-pressure turbine (HPT) case flange. We are issuing this AD to prevent failure of the diffuser-to-HPT case flange, which could lead to uncontained engine failure and damage to the airplane.

Affected ADs

This AD replaces AD 2014-05-32, Amendment 39-17804 (79 FR 17856, March 31, 2014).

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