Airworthiness directives › 2018-17-15
AD 2018-17-15 Airworthiness Directives; Honeywell International Inc. Turboprop and Turboshaft Engines
Applicability*9
This AD applies to Honeywell International Inc. (Honeywell) TPE331-1, -2, -2UA, -3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -8, -10, -10AV, -10GP, -10GT, -10N, -10P, -10R, -10T, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, and -11U, -12B, -12JR, -12UA, -12UAR, -12UHR, -25AA, -25AB, -25DA, -25DB, -25FA, -43-A, -43-B, -47-A, -55-B, and -61-A turboprop engine models, including those engine models with a -L stamped after the model number (for example, -43-BL); and TSE331-3U turboshaft engine models with combustion chamber case assemblies, part numbers (P/Ns) 869728-x, 893973-x, 3101668-x, and 3102613-x, where “x” denotes any dash number, installed.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
(1) For all affected engines: (i) Inspect all accessible areas of the combustion chamber case assembly, focusing on the weld joints, before accumulating 450 hours time in service (TIS) since last fuel nozzle inspection or within 50 hours TIS after the effective date of this AD, whichever occurs later. (ii) Perform the inspection in accordance with the Accomplishment Instructions, paragraphs 3.B.(1) through 3.B.(2), in Honeywell Service Bulletin (SB) TPE331-72-2178, Revision 0, dated May 3, 2011, or SB TPE331-72-2179, Revision 0, dated May 3, 2011, as applicable to the affected engine model. (iii) Thereafter, repeat this inspection during scheduled fuel nozzle inspections at intervals not to exceed 450 hours TIS since the last fuel nozzle inspection. (2) For TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, and -6A engine models with combustion chamber case assemblies, P/Ns 869728-1, 869728-3, or 893973-5, installed, and without the one-piece bleed pad with P3 boss; and for TPE331-1, -2, and -2UA engine models modified by National Flight Services, Inc., supplemental type certificate (STC) SE383CH, remove the combustion chamber case assembly from service at the next removal of the combustion chamber case assembly from the engine, not to exceed 3,700 hours TIS since last hot section inspection. (3) After the effective date of this AD, do not weld repair the applicable combustion chamber case assemblies unless the weld repair procedures are approved by the Manager, Los Angeles ACO Branch, and that approval specifically refers to this AD.
Unsafe condition
This AD was prompted by reports that combustion chamber case assemblies have cracked and ruptured. We are issuing this AD to prevent failure of the combustion chamber case assembly. The unsafe condition, if not addressed, could result in failure of the combustion chamber case assembly, in-flight shutdown, and reduced control of the airplane.
Affected ADs
This AD replaces AD 2018-02-14, Amendment 39-19167 (83 FR 3263, January 24, 2018).
Read the original on the Federal Register →
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