2018-13-05: Turbine Engine Reduction Gear

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 adding the following new airworthiness directive (AD): 2018-13-05 Honeywell International Inc. (Type Certificate previously held by AlliedSignal, Garrett Engine Division; Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona): Amendment 39-19317; Docket No. FAA-2016-9450; Product Identifier 2016-NE-25-AD. (a) Effective Date This AD is effective July 26, 2018. (b) Affected ADs None. (c) Applicability This AD applies to Honeywell International Inc. (Honeywell) TPE331-1, -2, -2UA, -3U, -3UW, -5, -5B, -6, -6A, -8, -10, -10AV, - 10N, -10P, -10R, -10T, -10U, -10UA, -10UF, -10UR model turboprop and TSE331-3U turboshaft engines with hydraulic torque sensor gear assemblies, part numbers (P/Ns) 3101726-1, -2, or -3, installed. [[Page 28766]] (d) Subject Joint Aircraft System Component (JASC) Code 7210, Turbine Engine Reduction Gear. (e) Unsafe Condition This AD was prompted by recent reports of failures of the direct drive fuel control gears and bearings in the hydraulic torque sensor gear assembly, P/N 3101726-3. We are issuing this AD to prevent failure of the hydraulic torque sensor gear assembly. The unsafe condition, if not addressed, could result in failure of the hydraulic torque sensor gear assembly, in-flight shutdown, and reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Oil Filter Sampling and Analysis (1) Obtain an initial engine oil filter sample of the affected engines within 150 hours time in service after the effective date of this AD. You can find guidance for obtaining oil filter samples in Honeywell's engine training manuals; for example, see the TPE331 Line Maintenance Training Manual. (2) Submit the engine oil filter sample within 3 days of sampling to an ISO/IEC 17025-accredited laboratory capable of performing analysis using ASTM D5185, Standard Test Method for Multielement Determination of Used and Unused Lubricating Oils and Base Oils by Inductively Coupled Plasma Atomic Emission Spectrometry (ICP-AES). You can find a list of Honeywell-authorized laboratories capable of performing this analysis in paragraph 1.D.(10) of Honeywell Service Information Letter (SIL) P331-97, Revision 11, dated July 23, 2008. (3) Perform an oil filter analysis for wear metals and evaluate filter contents using paragraphs 1.D.(4) and (5) of Honeywell SIL P331-97, Revision 11, dated July 23, 2008. Guidelines for interpreting analysis results can be found in paragraph (8) of Honeywell SILP331-97. (4) For those engines where the oil filter analysis indicates the need for an inspection or resample, as specified in Figures 1, 2 or 3 of the Honeywell SIL P331-97, Revision 11, dated July 23, 2008, accomplish the following: (i) If Figures 1, 2, or 3 indicate an inspection is required, within 5 days after receiving notification from the laboratory that performed the analysis, inspect the torque sensor gear assembly using paragraph (g)(4)(iii) of this AD. (ii) If Figures 1, 2, or 3 indicate a resample is required, perform a repeat oil filter sample and analysis, within 25 hours time in service after receiving notification from the laboratory that performs the analysis to evaluate for wear metals in accordance with paragraphs (g)(1), (2) and (3) of this AD. (A) If the resample indicates a second resample or inspection is required, within 5 days after receiving notification from the laboratory that performed the analysis, inspect the hydraulic torque sensor gear assembly using paragraph (g)(4)(iii) of this AD. (B) Reserved. (iii) Inspect the hydraulic torque sensor gear assembly using the following steps: (A) Remove bearings, P/Ns 358893-1, 3103035-1, 3103585-1 or 70100168-1, from the assembled spur gear and fuel control drive gearshaft and inspect or replace. Guidance for performing the inspection can be found in Section 70-00-00, Standard Practices of the applicable TPE331 engine maintenance manual. For example, see paragraph 5., ``Bearing Inspection,'' on pages 11-12 of Honeywell Maintenance Manual 70-00-00, TPE331-10 (Report No. 72-00-27), dated February 29, 2000. (B) Visually inspect the gearshaft teeth for scoring, pitting, chipping, metal deposits or corner breakage. Visual defects on gear teeth are acceptable if defects cannot be felt using a 0.031 inch diameter stylus. No corner breakage is allowed. (5) Thereafter, repeat the steps identified in paragraphs (g)(1) through (4) of this AD every additional 150 hours time in service after last oil filter sampling. (6) For any hydraulic torque sensor gear assembly that fails the inspection required by paragraph (g) of this AD, remove the affected hydraulic torque sensor gear assembly and, before further flight, replace with a part eligible for installation. (h) Hydraulic Torque Sensor Gear Assembly Overhaul After the effective date of this AD, do not use the Honeywell Torque Sensor Gear Assembly Overhaul Manual with Illustrated Parts List, 72-00-17, Revision No. 9, dated, July 20, 1992, or earlier versions, to overhaul TPE331 or TSE331 hydraulic torque sensor gear assemblies, P/Ns 3101726-1, -2, or -3. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles ACO Branch, 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 (j) of this AD. (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. (j) 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. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Honeywell Service Information Letter P331-97, Revision 11, dated July 23, 2008. (ii) Reserved. (3) For Honeywell service information identified in this AD, contact Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 85034-2802; phone: 800-601-3099; internet: https://myaerospace.honeywell.com/wps/portal. (4) You may view this service information at FAA, Engine and Propeller Standards Branch, Policy and Innovation Division, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7759. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.