2018-22-01: Turbine Section

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 88-12-10, Amendment 39-5910 (53 FR 19766, May 31, 1988), and adding the following new AD: 2018-22-01 Honeywell International Inc. (Type Certificate previously held by AlliedSignal Inc., Garrett Engine Division; Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona): Amendment 39-19474; Docket No. FAA-2018-0216; Product Identifier 1988-ANE-18-AD. (a) Effective Date This AD is effective December 10, 2018. (b) Affected ADs This AD replaces AD 88-12-10, Amendment 39-5910 (53 FR 19766, May 31, 1988). (c) Applicability This AD applies to Honeywell International Inc. (Honeywell) TPE331-8, -10, -10N, -10R, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, and -11U turboprop engines with second stage turbine rotor assemblies, part number (P/Ns) 3102106-1, -6, and -8 or P/N 3101514- 1, -10 and -12, installed. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by a report that a TPE331-11U engine installed on an M7 Aerospace LP SA227 airplane experienced an uncontained rotor separation and the discovery of cracks in the bore of the second stage turbine rotor assembly after publication of AD 88-12-10. We are issuing this AD to prevent failure of the second stage turbine rotor. The unsafe condition, if not addressed, could result in uncontained release of the second stage turbine rotor, damage to the engine, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unlessalready done. (g) Required Actions (1) Remove from service the applicable second stage turbine rotor assembly, P/Ns 3102106-1, -6 and -8, according to the schedule in Table 1 to Paragraph (g)(1) of this AD: Table 1 to Paragraph (g)(1) of This AD--Removal of Second Stage Rotor, P/ Ns 3102106-1, -6 and -8 ------------------------------------------------------------------------ Second stage turbine rotor cycles since new (CSN) on the effective Removal schedule date of the AD ------------------------------------------------------------------------ 0 to 2,600........................ Prior to 3,000 CSN. 2,601 to 3,300.................... Within 400 cycles-in-service (CIS) after the effective date of this AD or 3,600 CSN, or at next access, whichever occurs first. 3,301 to 4,000.................... Within 200 cycles-in-service after the effective date of this AD or 4,100 CSN, or at next access, whichever occurs first. 4,001 to 4,800.................... Within 100 cycles-in-service after the effective date of this AD or 4,800 CSN, or at next access, whichever occurs first. ------------------------------------------------------------------------ (2) Remove from service the applicable second stage turbine rotor assembly, P/Ns 3101514-1, -10 and -12, per the schedule in Table 2 to Paragraph (g)(2) of this AD: Table 2 to Paragraph (g)(2) of This AD--Removal of Second Stage Rotors, P/Ns 3101514-1, -10 and -12 ------------------------------------------------------------------------ Second stage turbine rotor CSN on the effective date of the AD Removal schedule ------------------------------------------------------------------------ 0 to 2,600........................ Prior to 3,000 CSN. 2,601 to 3,200.................... Within 400 CIS after the effective date of this AD or 3,600 CSN, or at next access, whichever occurs first. 3,201 to 3,800.................... Within 200 CIS after the effective date of this AD or 4,100 CSN, or at next access, whichever occurs first. 3,801 to 4,400.................... Within 100 CIS after the effective date of this AD or 4,400 CSN, or at next access, whichever occurs first. ------------------------------------------------------------------------ [[Page 55258]] (h) Definition For the purpose of this AD, ``next access'' is defined as when the applicable second stage turbine rotor assembly is removed from the engine. (i) Installation Prohibition As of the effective date of this AD, do not install second stage turbine rotor assemblies, P/Ns 3102106-1, -6, and -8 and P/Ns 3101514-1, -10, and -12 on any engine. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles ACO, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (k) of this AD. You may email your request to: 9-ANM-LAACO-AMOC-REQUESTS@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (k) Related Information For more information about this AD, contact Joseph Costa, Aerospace Engineer, Los Angeles ACO Branch, FAA, 3960 Paramount Blvd., Lakewood, CA 90712-4137; phone: 562-627-5246; fax: 562-627- 5210; email: joseph.costa@faa.gov. (l) Material Incorporated by Reference None.