Airworthiness directives › 2023-22-02
AD 2023-22-02 Airworthiness Directives; Pratt & Whitney Division Engines
Models named: PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, PW4090-3. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Pratt & Whitney Division (PW) Model PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 engines.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
(1) Within the compliance times specified in paragraphs (g)(1)(i) though (iii) of this AD, perform an initial high sensitivity fluorescent penetrant inspection (FPI) of the ODC T3 thermocouple probe boss (Tt3 boss) for crack indications in accordance with the Accomplishment Instructions, paragraph 1.F. of Part A or paragraph 1.B. of Part B, as applicable, of PW Alert Service Bulletin PW4G-112-A72-347, Revision 4, dated September 1, 2022 (ASB PW4G-112-A72-347, Rev 4). (i) For an ODC that has accumulated less than 12,000 cycles since new (CSN) with no prior high sensitivity FPI of the ODC Tt3 boss, perform the high sensitivity FPI before accumulating 9,200 CSN or within 1,000 flight cycles (FCs), after the effective date of this AD, whichever occurs later. (ii) For an ODC with unknown CSN or an ODC that has accumulated 12,000 CSN or more with no prior high sensitivity FPI of the ODC Tt3 boss, perform the high sensitivity FPI before accumulating 13,000 CSN or within 1,000 FCs, after February 26, 2018 (the effective date of AD 2018-02-10), whichever occurs later. (iii) For an ODC that has undergone a high sensitivity FPI of the ODC Tt3 boss prior to the effective date of this AD that resulted in no crack indication, perform the high sensitivity FPI before accumulating 2,000 FCs since performance of the last FPI or during the next engine shop visit, whichever occurs first. (iv) For an ODC that has undergone a high sensitivity FPI of the ODC Tt3 boss prior to the effective date of this AD that resulted in an indication of a crack, perform the actions required by paragraphs (g)(3)(i) through (iii) of this AD, as applicable. (2) Thereafter, repeat the high sensitivity FPI of the ODC Tt3 boss at each engine shop visit or before exceeding 2,000 FCs from the last high sensitivity FPI of the ODC Tt3 boss, whichever occurs first, in accordance with the Accomplishment Instructions, paragraphs 1.F. of Part A or paragraph 1.B. of Part B, as applicable, of ASB PW4G-112-A72-347, Rev 4. (3) If, during any inspection required by paragraphs (g)(1) or (2) of this AD, there is any crack indication, perform the actions specified in paragraphs (g)(3)(i) through (iii) of this AD. (i) For engines installed on an aircraft, repeat the high sensitivity FPI or remove the ODC from service in accordance with the actions and compliance times specified in the Accomplishment Instructions, Part A, paragraphs 1.G. and 1.H., of ASB PW4G-112-A72-347, Rev 4. (ii) For engines not installed on an aircraft, repeat the high sensitivity FPI or remove the ODC from service in accordance with the actions and compliance times specified in the Accomplishment Instructions, Part B, paragraphs 1.C. and 1.D., of PW ASB PW4G-112-A72-347, Rev 4. (iii) For engines at an engine shop visit, before further flight, remove the ODC from service. (4) Within 30 days after the effective date of this AD, revise the Airworthiness Limitations Section (ALS) of the existing engine maintenance manual or Instructions for Continued Airworthiness and the existing approved maintenance program, as applicable, to include the piece-part inspections of the ODC as defined in Table 1 to paragraph (g)(4) of this AD. Table 1 to Paragraph (g) (4)—Addition to ALS Description Part No. Cleaning, inspection and repair (CIR) manual section CIR manual inspection CIR manual Case, Diffuser, Outer All 72-41-13 Inspection/Check (I/C-02) P/N 51A750 (5) For engines with ODC part number (P/N) 50J775 or 50J930 installed, at the next piece-part exposure after the effective date of this AD, replace the ODC with a part eligible for installation.
Unsafe condition
This AD was prompted by the discovery of multiple cracked outer diffuser cases (ODCs). We are issuing this AD to prevent failure of the ODC. This condition, if not addressed, could result in failure of the ODC, damage to the engine, and damage to the airplane.
Affected ADs
This AD replaces AD 2018-02-10, Amendment 39-19163 (83 FR 2896, January 22, 2018).
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