SERVICE BULLETIN Engines, Systems & Services Phoenix, Arizona

Transcription

1 REVISION TRANSMITTAL SHEET This sheet transmits Revision 27 to Service Bulletin No. titled ENGINE Service Life Limits of Critical Life Limited Components, and Periodic Maintenance Schedules. This is a COMPLETE reissue. This bulletin has been reprinted in its entirety. Please remove and discard all pages of prior issues and replace with pages of this revision. Reason for Revision: NOTE: This revision DOES NOT require further action if in compliance with a previous issue. This service bulletin is revised to add an engine model number, update aircraft application, and update to current format. Section 1 Section 2 Title page is revised to reflect latest revision date. Paragraphs 1.A and 1.J are revised to add Engine Model No. TPE331-12JR-701S. Section 2, Table of Contents, is revised to change reference from TPE331-12JR-701C to TPE331-12JR in Table 2A title. Updated revision number references to. Table 2A is revised to change reference from TPE331-12JR-701C to TPE331-12JR in title. Table 2A is revised to add reference to Service Bulletin TPE331-A for Gearbox inspection and Overhaul Engine or accomplish CAM inspection. Paragraph 2.J is revised to delete the annual per aircraft utilization requirement, clarify the applicability of service bulletins listed in Table 5 or 6, explain why some engines are not listed in the effectivity section of some service bulletins, and to delete paragraph regarding reporting of information. Paragraph 2.J and Step 2.J.(1) are revised to add time limit for compliance of service bulletins in Table 5 or 6. Table 7 is revised to add reference to Service Bulletin TPE331-A for Reduction Gear Section. Table 7 is revised to add Fuel Control Assembly Overhaul/CAM intervals for TPE331-12JR-701S. Paragraph 2.K is revised to delete the annual per aircraft utilization requirement. Sept 17/03 Page 1 of 2

2 List of Effective Pages Page No. Date Page No. Date 1 Sept 17/03 24 Sept 17/03 2 Sept 17/03 25 Sept 17/03 3 May 24/02 26 Sept 17/03 4 Sept 17/03 27 Sept 17/03 5 May 24/02 28 May 24/02 6 Sept 17/03 29 May 24/02 7 May 24/02 30 May 24/02 8 May 24/02 31 May 24/02 9 May 24/02 32 May 24/02 10 May 24/02 33 July 26/02 11 May 24/02 34 May 24/02 12 May 24/02 35 Sept 17/03 13 May 24/02 36 May 24/02 14 May 24/02 37 Sept 17/03 15 July 26/02 38 Sept 17/03 16 May 24/02 39 Sept 17/03 17 May 24/02 40 Sept 17/03 18 May 24/02 41 Sept 17/03 19 May 24/02 42 May 24/02 20 May 24/02 43 Sept 17/03 21 May 24/02 44 May 24/02 22 May 24/02 45 Sept 17/03 23 Sept 17/03 46 May 24/02 Previous Revisions Revision 1 dated Jan 23/87 Revision 2 dated Dec 9/87 Revision 3 dated Sept 21/88 Revision 4 dated Feb 17/89 Revision 5 dated July 7/89 Revision 6 dated Mar 2/90 Revision 7 dated Sept 14/90 Revision 8 dated Nov 9/90 Revision 9 dated Mar 22/91 Revision 10 dated Sept 20/91 Revision 11 dated Dec 6/91 Revision 12 dated Apr 17/92 Revision 13 dated July 31/92 Revision 14 dated Feb 19/93 Revision 15 dated May 10/93 Revision 16 dated Sept 3/93 Revision 17 dated Apr 22/94 Revision 18 dated July 11/94 Revision 19 dated Nov 26/97 Revision 20 dated Aug 5/98 Revision 21 dated Sept 7/98 Revision 22 dated Oct 16/98 Revision 23 dated Sept 6/99 Revision 24 dated Dec 8/99 Revision 25 dated May 24/02 Revision 26 dated July 26/02 Sept 17/03 Page 2 of 2

3 Category 1: Safety ENGINE SERVICE LIFE LIMITS OF CRITICAL LIFE LIMITED COMPONENTS, AND PERIODIC MAINTENANCE SCHEDULES WARNING: COMPONENTS IDENTIFIED IN SECTION 2.D. OF THIS SERVICE BULLE- TIN CURRENTLY HAVE FAA CERTIFIED LIFE LIMITS, AND MUST BE REPLACED BY THE LIMITS STATED WITHIN THE SERVICE BULLETIN. HONEYWELL WILL NOT AUTHORIZE OPERATION BEYOND THE LIFE LIMITS PRESENTED HEREIN, AND THESE LIFE LIMITS CANNOT BE EXTENDED BY THE INDIVIDUAL OPERATORS. IT IS THE RESPONSIBIL- ITY OF EACH OPERATOR TO ENSURE THAT LIFE LIMIT RECORDS FOR COMPONENTS IDENTIFIED IN THIS SERVICE BULLETIN ARE CORRECT AND COMPLETE. LIFE LIMITED COMPONENTS WITH NO RECORDED HOUR OR CYCLE TRACEABILITY SHALL BE IMMEDIATELY REMOVED FROM SERVICE. OPERATION OF AN ENGINE WITH COMPONENTS THAT EXCEED THE LIFE LIMITS IDENTIFIED IN THIS SERVICE BULLETIN CREATES SUB- STANTIAL RISK TO LIFE AND PROPERTY. SUCH AN ENGINE, FOR EX- AMPLE, MAY MALFUNCTION IN A WAY THAT LEADS TO STRUCTURAL FAILURE. SUCH A FAILURE COULD INVOLVE EJECTION OF METAL FRAGMENTS FROM THE ENGINE, COULD BE CATASTROPHIC AND COULD LEAD TO SERIOUS INJURY OR DEATH. HONEYWELL EXPRESSLY DISCLAIMS LIABILITY FOR ANY AND ALL INJURY OR DEATH TO PERSONS OR DAMAGES TO PROPERTY, DI- RECTLY OR INDIRECTLY CAUSED BY AN ENGINE THAT IS OPERATED WITH COMPONENTS THAT EXCEED THE CYCLE LIFE LIMITS IDENTI- FIED IN THIS SERVICE BULLETIN. HONEYWELL FURTHER DISCLAIMS LIABILITY FOR ANY AND ALL INDIRECT, CONSEQUENTIAL OR INCIDEN- TAL DAMAGES, AND WILL SEEK INDEMNITY FROM YOU FOR ANY SUCH DAMAGES. 1. Planning Information A. Effectivity This service bulletin is applicable to the following turboprop aircraft engines. Part No. Model No. Serial No. Application TPE K NA No Current Application TPE331-12B-701A All Shorts Basic Trainer TPE331-12B-702A All Shorts Basic Trainer TPE331-12B-703A All Shorts Basic Trainer /-3 TPE331-12JR-701C All CASA /-4 TPE331-12JR-702C All No Current Application Revision 27, Sept 17/03 Copyright 1984, 2003 Honeywell International Inc. All rights reserved. Page 1 of 46

4 Part No. Model No. Serial No. Application TPE331-12JR-701S All Aero Twin Inc Caravan TPE331-12UA-701G All Metro III/ /-4/-8/-9 TPE331-12UAR-701G All Metro III/ /-12/-32/ TPE331-12UAR-701H All Jetstream /-13/-33/ TPE331-12UAR-702H All Jetstream /-14/-34/ TPE331-12UAR-703H All Jetstream /-15/-35/ TPE331-12UAR-704H All Jetstream /-16/-36/ TPE331-12UAR-705H All Jetstream /-17/-37/ TPE331-12UAR-706H All Jetstream /-18/-38/ TPE331-12UAR-707H All Jetstream /-19/-39/ TPE331-12UAR-708H All Jetstream TPE331-12UER-701H NA No Current Application /-7/-11/-12 TPE331-12UHR-701G All Metro /-24/-48/ TPE331-12UHR-701H All Jetstream /-25/-49/ TPE331-12UHR-702H All Jetstream /-26/-50/ TPE331-12UHR-703H All Jetstream /-27/-51/ TPE331-12UHR-704H All Jetstream /-30/-56/ TPE331-12UHR-705H All No Current Application /-31/-57/ -59 TPE331-12UHR-706H All No Current Application Revision 27, Sept 17/03 Page 2

5 1. B. Reason This service bulletin provides FAA approved life limits of certain critical components, a listing of time/cycle tracked components, periodic engine maintenance schedules, and instructions for providing information to Honeywell Engines, Systems & Services when life limited and time/cycle tracked components are removed from service. Maintenance procedures are located in the Engine Maintenance Manual, Inspection/Repair Manual, and Engine/ Component Overhaul Manuals. The service life and reliability of any specific engine depends on many factors which vary with type of service, operating technique, ambient conditions, and maintenance practices. The condition of any specific engine should be constantly evaluated by the operator based on the operational history of the engine consistent with the above. Operators may therefore find it necessary to accomplish major inspections and/or overhaul engines prior to the specified time if such action is indicated considering mechanical condition, operational characteristics and/or performance. Testing, operational experience, and evaluation by the manufacturer has established that certain parts are service-limited, with such limit being determined by time or cycles in service, or physical condition as evidenced by inspection. Such parts must be replaced dependent on time or cycles in service and/or physical condition. The tabulation of maintenance intervals as set out in this service bulletin is approved by the engine manufacturer, and should be considered in light of the comments above. Continuous Airworthiness Maintenance may be implemented for engines in commercial service. Disassembly and inspection of the engine at specified intervals (with component parts replaced or repaired as required) will ensure engine reliability at a minimal overall maintenance cost. Engine inspections and appropriate parts replacement form the basis of the program. C. Description This service bulletin provides: D. Compliance FAA approved life limits for certain critical components a listing of time/cycle tracked components bearing assembly, and other component replacement schedules a listing of periodic inspection and maintenance requirements requirements for Time Between Overhaul (TBO) requirements for Continuous Airworthiness Maintenance (CAM). Compliance addresses a safety issue. Recommended. TBO and CAM maintenance intervals specified in this service bulletin are the manufacturer s approved intervals. Individual regional airline operators may extend these intervals only with the approval of their local FAA Flight Standards District Office (FSDO) or appropriate airworthiness regulating authority. (Refer to Section 2, Paragraph K.) Page 3

6 1. E. Approval Section 2, Accomplishment Instructions, is FAA approved. F. Manhour Requirements Not applicable. G. Material - Price and Availability Not applicable. H. Tooling - Price and Availability Not applicable. I. Weight and Balance Not applicable. J. Publications References The sources of information used in the preparation of this service bulletin include Honeywell engineering documentation and the following. Part/ Model No. Revision 27, Sept 17/03 Engine Overhaul Manual Engine Maintenance Manual Illustrated Parts Catalog TPE K NA NA NA TPE331-12B-701A TPE331-12B-702A TPE331-12B-703A TPE331-12JR-701C TPE331-12JR-702C NA NA NA TPE331-12JR-701S TPE331-12UA-701G TPE331-12UAR-701G TPE331-12UAR-701H TPE331-12UAR-702H TPE331-12UAR-703H TPE331-12UAR-704H TPE331-12UAR-705H TPE331-12UAR-706H TPE331-12UAR-707H Page 4

7 Part/ Model No. Engine Overhaul Manual Engine Maintenance Manual Illustrated Parts Catalog TPE331-12UAR-708H TPE331-12UER-701H NA NA NA TPE331-12UHR-701G TPE331-12UHR-701H TPE331-12UHR-702H TPE331-12UHR-703H TPE331-12UHR-704H TPE331-12UHR-705H NA TPE331-12UHR-706H NA 1. K. Service Bulletin References None. L. Other Publications Affected Inspection/Repair Manual, Report No. 72-IR-15. Page 5

8 TABLE OF CONTENTS SECTION 2 - ACCOMPLISHMENT INSTRUCTIONS PARAGRAPH PAGE General Information 7 Update Life Limited Part Log Card A 8 Initiate New Life Limited Part Log Card B 9 Return Life Limited Part Log Card C 11 Replace Critical Components Within FAA Certified Life Limits (Cycles) D 13 Maintain Life Limited or Maint/Mod Record Card E 14 Return Life Limited or Maint/Mod Record Card (Life Tracked Parts) F 15 Bearing Assembly Replacement Schedule G 17 Periodic Inspection Requirements H 19 Time Between Overhaul (TBO) Requirements I 34 (Commercial Operation) TBO and CAM Maintenance Requirements J 38 Inspection Interval Extension K 45 SECTION 2 - TABLES TABLE NO. PAGE Bearing Assembly Replacement Schedule 1 17 Periodic Inspection Requirements TPE331-12B 2 19 TPE331-12JR, TPE331-12UA/-12UAR/-12UHR-701G 2A 23 TPE331-12UA, TPE331-12UAR/-12UHR-701H thru -708H 2B 28 Minimum Service Bulletin Compliance Requirements for TBO and CAM 3000 Hour TBO and 5000 Hour TBO 3 35 (Commercial Operation) 7000 Hour TBO 5 39 (Commercial Operation) 7000 Hour CAM 6 41 Maintenance Requirements for TBO or CAM 3000 Hour and 5000 Hour TBO 4 37 (Commercial Operation) 7000 Hour TBO or CAM 7 43 Revision 27, Sept 17/03 Page 6

9 2. Accomplishment Instructions NOTE: Engine Model TPE K has been deleted from the accomplishment instructions. Engine Model TPE331-12UER-701H has no current application. Publications listed in Section 1 provide applicable disassembly, cleaning, inspection, reassembly, and testing instructions, and must be referred to during the accomplishment of the following instructions. The engine must be maintained and inspected in accordance with the applicable engine manuals and requirements of this service bulletin. Definition of Hours (Engine Operating Hours): Any time the engine is operated in flight (liftoff to touchdown). Definition of Cycles: Any operating sequence involving engine start, aircraft takeoff and landing, and engine shutdown. CAUTION: (ENGINES WITH APR OR RPR) THE AUTOMATIC PERFORMANCE RESERVE (APR) OR RESTRICTED POWER RESERVE (RPR) SYSTEM IS AUTHORIZED FOR USE ONLY DURING EMERGENCY CONDI- TIONS. WHENEVER APR OR RPR IS USED IN FLIGHT, THE TIME AND CYCLES MUST BE RECORDED IN THE ENGINE LOG BOOK. FIFTY (50) HOURS MUST BE RECORDED IN THE ENGINE LOG BOOK FOR EACH ACCUMULATED HOUR OF APR OR RPR OPERATION. IN COMPUTING ACCUMULATION OF TIME INCREMENTS OF LESS THAN ONE (1) HOUR, THE PENALTY TIME SHALL BE CALCULATED AS FOLLOWS: APR OR RPR TIME (IN MINUTES) DIVIDED BY 60, MULTIPLIED BY 50, EQUALS PENALTY TIME (IN HOURS). THE PENALTY HOURS MUST BE INCLUDED IN ACCUMULATION OF HOURS TOWARD TURBINE (HOT) SECTION INSPECTION. FOUR (4) CYCLES MUST BE RECORDED ON LIFE LIMITED PART LOG CARDS AND IN THE ENGINE LOG BOOK, AGAINST LIFE LIMITED PART SERIAL NUMBERS, EACH TIME APR/RPR IS USED. Service life limits of critical parts are based on engines being operated within approved operating limits, and being maintained in accordance with Honeywell published instructions. A record of engine operating hours and cycles shall be maintained in the engine log book. Life limited part log cards are required to provide a history of critical parts. A life limited part for which no history can be determined, must be removed from service. For each cycle life limited component, the number of accumulated cycles must be recorded against the component part number and serial number in the engine log book and on the applicable life limited part log card. This shall be accomplished at scheduled and unscheduled component inspections, and at installation on and removal from the engine. Page 7

10 In the event of an operating period during which operating cycles have not been recorded, but operating hours can be determined, the FAA Los Angeles Aircraft Certification Office (LAACO) has approved debiting the life limited components with four (4) cycles per operating hour as an alternate method of compliance for cycle recording. The FAA LAACO has informed Honeywell that operators who do not comply, and who want to use a different conversion factor, should submit their request for an alternate method of compliance to the FAA LAACO along with their substantiation for using a conversion factor other than four (4) cycles per operating hour. If additional life limited part log cards are needed, contact Honeywell Engines, Systems & Services, Data Distribution, M/S 64-03/ , P.O. Box 52170, Phoenix, AZ Deviation from the following procedures for updating and initiating life limited part log cards requires prior approval from local FAA Flight Standards District Office (FSDO), or equivalent airworthiness authority Parts which require Hour/Cycle tracking but which are not life limited, are exempt from this procedure. Previously issued life limited part log cards have a different heading for Blocks (10) and (16) than shown in Figure 1. A signature and FAA number are now required in Blocks (10) and (16), although the column heading on older cards is Remarks. NOTE: Updating the life limited part log card is required any time a life limited part is installed on, or removed from, an engine. 2. A. Update Life Limited Part Log Card (See Figure 1) (1) Update the life limited part log card for a new (zero time) life limited part installed on an engine. (See Figure 1.) (a) Verify that data in Blocks (1) thru (3) is correct. (b) Enter date that part was installed on the engine in Block (4). (c) Enter engine serial number in Block (5). (d) Enter zero (0) in Blocks (6) thru (9). (e) Sign name and enter FAA number in Block (10). (f) No further entries are required until the part is removed from the engine. (2) Update the life limited part log card for a used life limited part installed on an engine. (See Figure 1.) (a) Verify that Blocks (1) thru (19) have been previously filled out, and that the data in Blocks (1) thru (3) is correct. (b) Enter date that part was installed on the engine in Block (4). (c) Enter engine serial number in Block (5). (d) Enter zero (0) in Blocks (6) and (7). Page 8

11 2. A. (2) (e) Enter total time (cycles and hours) on the part in Blocks (8) and (9). (f) Sign name and enter FAA number in Block (10). (g) No further entries are required until the part is removed from the engine. (3) Update the life limited part log card for a life limited part removed from an engine. (See Figure 1.) (a) (b) Verify that Blocks (1) thru (9) have been previously filled out, and that the data in Blocks (1) thru (3) is correct. Verify that Block (10) has a signature and FAA number. (c) Enter date that part was removed from the engine in Block (11). (d) Enter time (cycles and hours) since part was installed on the engine in Blocks (12) and (13). (e) Enter total time (cycles and hours) on part in Blocks (14) and (15). (f) Sign name and enter FAA number in Block (16). B. Initiate New Life Limited Part Log Card (See Figure 1) There are certain instances when initiation of a new life limited part log card may be necessary: new engines delivered with life limited part log cards lost or unavailable repaired engines with life limited parts installed and no life limited part log cards provided engines containing turbine disks or rotor assemblies whose times in service have been converted from hours to cycles spare parts for which no life limited part log cards have been provided. (1) Initiate Life Limited Part Log Cards for Life Limited Parts Installed on a New Engine or for a New Spare Part Without a Life Limited Part Log Card. (See Figure 1.) (a) Fill in Blocks (1) thru (5) from information provided on critical parts list, included in the engine log book, and D.S.C. (Data Sheet, Customer), for each life limited part. (b) Enter zero (0) in Blocks (6) and (7). (c) Sign name and enter FAA number in Block (10). (d) No further entries are required until the part is removed from the engine. Page 9

12 NOTE: Life Limited Components with no recorded time or cycle traceability shall be removed from service. Refer to Paragraph 2.D. 2. B. (2) Initiate Life Limited Part Log Cards for Life Limited Parts Installed on a Repaired Engine and no Life Limited Part Log Cards Provided. (See Figure 1.) (a) Fill in Blocks (1) thru (5) from information provided on critical parts list, included in the engine log book and build documents, for each life limited part. (b) Enter zero (0) in Blocks (6) and (7). (c) Enter total time (cycles and hours) on part, when part was installed on the engine, in Blocks (8) and (9). (d) Enter date engine was repaired in Blocks (4) and (17). (e) Enter method used to determine total time (hours and cycles) in Block (18). (f) Sign name and enter FAA number in Blocks (10) and (19). NOTE: Life Limited Components with no recorded time or cycle traceability must be removed from service. Refer to Paragraph 2.D. (3) Initiate Life Limited Part Log Cards for Life Limited Parts, Time in Service Converted From Hours to Cycles, Installed on a Repaired Engine and no Life Limited Part Log Cards Provided. (See Figure 1.) (a) Fill in Blocks (1) thru (5) from information provided on critical parts list, included in the engine log book, or build documents if the parts were installed at repair or at scheduled maintenance, for each life limited part. (b) Enter zero (0) in Blocks (6) and (7). (c) Enter total time (cycles and hours) on the part in Blocks (8) and (9). (d) Enter date part was installed on the engine in Blocks (4) and (17). (e) Enter method used to determine time (hours and cycles) in Block (18). (f) Sign name and enter FAA number in Blocks (10) and (19). Page 10

13 2. C. Return Life Limited Part Log Card to Honeywell NOTE: When life limited parts are removed from service, please provide the following to Honeywell Engines, Systems & Services, Reliability, Safety, and Maintainability, Dept 93-42/551-18, P.O. Box 52181, Phoenix, AZ (1) Life limited part log card. If a card is not available, initiate card as shown in Figure 1 and enter all available data on the card. (a) (b) (c) (d) Part number of part. Serial number of part. Hours or cycles on part. Reason for removing part. Page 11

14 Life Limited Part Log Card and Maintenance Record Figure 1 Page 12

15 2. D. Replace Critical Components Within FAA Certified Life Limits (Cycles) WARNING: THE FOLLOWING COMPONENTS HAVE FAA CERTIFIED LIFE LIMITS AND MUST BE REPLACED WITHIN THE SPECIFIED LIFE LIMITS. THESE LIFE LIMITS CAN NOT BE EXTENDED BY INDI- VIDUAL OPERATORS. LIFE LIMITED COMPONENTS WITH NO RECORDED HOUR OR CYCLE TRACEABILITY MUST BE IMMEDIATELY REMOVED FROM SERVICE. REFER TO THE WARNING INFORMATION ON PAGE 1 OF THIS SERVICE BULLETIN. Component Part No. Operating Cycles First Stage Compressor Impeller /-3 30,000 First Stage Compressor Impeller /-2 30,000 *First Stage Compressor Impeller ,000 *First Stage Compressor Impeller ,000 *First Stage Compressor Impeller ,000 Second Stage Compressor Impeller /-3/-4 30,000 *First Stage Turbine Rotor Disk /-2/-3 10,000 *First Stage Turbine Rotor Disk /-2 10,000 *First Stage Turbine Rotor Disk ,000 *First Stage Turbine Rotor Disk ,000 *Second Stage Turbine Rotor Disk ,000 *Second Stage Turbine Rotor Disk /-4 10,000 *Second Stage Turbine Rotor Disk /-2 10,000 *Second Stage Turbine Rotor Disk ,000 *Second Stage Turbine Rotor Disk ,000 *Second Stage Turbine Rotor Disk ,000 *Second Stage Turbine Rotor Disk ,000 *Second Stage Turbine Rotor Disk /-2 10,000 Third Stage Turbine Rotor Assy /-3/-4 6,000 Third Stage Turbine Rotor Assy /-2 12,000 *Rotating Air Seal /-2 10,000 *Rotating Air Seal /-2/-5 20,000 *Rotating Air Seal /-3 20,000 *Rotating Air Seal ,000 Page 13

16 Component Part No. Operating Cycles *Rotating Air Seal ,000 *Rotating Air Seal ,000 *Rotating Air Seal ,000 *This part is a component of an assembly. Some Life Limited Part Log Cards have been initiated with only the assembly part number listed. In these cases the correct part number of the life limited component should be added to the Life Limited Part Log Card. The correct component part number can be determined by consulting the applicable Illustrated Parts Catalog or from the actual part itself. Only the component part, as listed in this service bulletin, is life limited. The assembly part number is included only to aid in traceability. 2. E. Maintain Life Limited Part Log Card or Component Maintenance/Modification Record Card for Identified Engine Component Parts Which Do Not Have FAA Certified Life Limits (See Figure 1 or 2) NOTE : Certain engine component parts do not have a finite cycle life limit assigned. Therefore, to provide a historical record of hours, cycles, service history and maintenance performed for the specified parts, a Life Limited Part Log Card or Component Maintenance/Modification Record Card must be maintained. If a part is removed, the Life Limited Part Log Card or Component Maintenance/Modification Record Card must be updated and stay with that part. Components already in service for which no Life Limited Part Log Card or Component Maintenance/Modification Record Card has been established, but for which history can be determined, must have life tracking established at next access to the affected part in conjunction with a maintenance action (scheduled or unscheduled). Component Part No. Note Bearings Refer to Table 1. Fuel Control Fuel Pump Fuel Shutoff Valve Propeller Governor Propeller Pitch Control Torque/Temperature Limiter Bypass Valve All All All All All All (If Installed) First Stage Turbine Rotor Blade Splined Spur Gearshaft (Bull) Splined Spur Gearshaft (Bull) Splined Spur Gearshaft (Bull) Splined Spur Gearshaft (Bull) Splined Spur Gearshaft (Bull) Page 14

17 Component Part No. Note Splined Spur Gearshaft (Bull) , 4 Splined Spur Gearshaft (Bull) Spur-Drive Gearshaft (Sun) /-2 2, 4, 5 Spur-Drive Gearshaft (Sun) , 5 High Speed Pinion , 4 High Speed Pinion High Speed Pinion Assembly , 4 High Speed Pinion Assembly /-11 3 Diaphragm Matched Housing Sets /-9 2, 3, 4 Diaphragm Matched Housing Sets Diaphragm Module Assembly /-10 2, 4 Diaphragm Module Assembly /-2 3 NOTE 1. NOTE 2. NOTE 3. NOTE 4. NOTE 5. A separate card must be maintained for each blade. Refer to Service Bulletin TPE331-A for detailed instructions. Refer to Service Bulletin TPE331-A for detailed instructions. Refer to Service Bulletin TPE331-A for detailed instructions. Accomplish a complete inspection (including gear tooth involute inspection, which must be done at a Honeywell authorized facility, in accordance with Inspection/Repair Manual, Report No. 72-IR-15) at engine overhaul or CAM inspection, not to exceed 7100 operating hours. 2. F. Return Life Limited Part Log Card or Component Maintenance/Modification Record Card to Honeywell NOTE: When time/cycle tracked parts are removed from service, please provide the following to Honeywell Engines, Systems & Services, Reliability, Safety, and Maintainability, Dept 93-42/551-18, P.O. Box 52181, Phoenix, AZ (1) Life limited part log card or component maintenance/modification record card. If card is not available, initiate card as shown in Figure 1 or 2 and enter all available data on card. (a) (b) (c) (d) Part number of part. Serial number of part. Hours or cycles on part. Reason for removing part. Revision 26, July 26/02 Page 15

18 COMPONENT MAINTENANCE / MODIFICATION RECORD CARD (RECORD CARD MUST TRAVEL WITH COMPONENT, REPAIR STATION OR ENGINE LOG BOOK) PART NOMENCLATURE PART NUMBER SERIAL NUMBER SERIES NUMBER CHANGE/MOD RECORD ENGINE SERIAL NO. AIRCRAFT SERIAL NO. ENGINE HOURS AT INSTALLATION ENGINE HOURS AT REMOVAL TOTAL HOURS ON PART DATE STATION REASON FOR REMOVAL COMPONENT MAINTENANCE / MODIFICATION RECORD CARD (SERVICE BULLETIN COMPLIANCE, REPAIRS, INSPECTIONS, ETC) DATE MAINTENANCE PERFORMED CHANGE/MOD RECORD AUTHORIZED SIGNATURE Component Maintenance/Modification Record Card Figure 2 SB1433 Page 16

19 2. G. Bearing Assembly Replacement Schedule CAUTION: INSTALL A NEW BEARING WHERE INDICATED BY + IN TABLE 1. THE ENGINE MANUFACTURER DOES NOT AUTHORIZE INSTALLATION OF ANY CONTINUED TIME, REMANUFACTURED, REPAIRED, OR RESTORED BEARING AT THOSE LOCATIONS NOTE: Bearing replacement intervals listed below are approved by the engine manufacturer. To provide a historical record of hours, cycles, service history and maintenance performed for the specified bearings, a Life Limited Part Log Card or Component Maintenance/Modification Record Card must be maintained. If bearing is removed, the Life Limited Part Log Card or Component Maintenance/Modification Record Card must be updated and stay with that bearing. Bearings already in service for which no Life Limited Part Log Card or Component Maintenance/Modification Record Card has been established, but for which history can be determined, need to have life tracking established at next removal of, or access to, the affected bearing in conjunction with a maintenance action (scheduled or unscheduled). Bearings already in service for which history is uncertain must be replaced at next major CAM inspection or overhaul, and life tracking must be established at that time. Bearings with a replacement interval of on condition, or with no maximum service life, may be reused indefinitely provided they meet inspection requirements detailed in Engine Maintenance Manual or Inspection/Repair Manual. They do not require Life Limited Part Log Cards or Component Maintenance/Modification Record Cards. Some bearings may have one or more asterisks (*) etched adjacent to the part number. Each asterisk indicates one engine overhaul or CAM inspection interval beyond the first OH/CAM. Table 1. Bearing Assembly Replacement Schedule Part No. Part Name Bearing Replacement Interval (TSN) Hours /-2 Turbine Roller Bearing (Rear Main Shaft) Each Turbine Section Inspection Matched Roller Bearing and Shaft Set On Condition (High Speed Pinion) # Matched Planet Gear and Bearing On Condition Helical Gearshaft Roller Bearing (Sun and Bull Gear) On Condition # /-3 Matched Planet Gear and Bearing On Condition Propeller Shaft Flanged Annular Ball Bearing On Condition Page 17

20 Part No. Table 1. Bearing Assembly Replacement Schedule (Cont) Part Name Bearing Replacement Interval (TSN) Hours Annular Ball Bearing (Matched Set) Each Engine Overhaul or major CAM inspection /-6 Compressor Bearing Bearing, Ball, Duplex Double Row Roller Bearing Turbine Roller Bearing (Rear Main Shaft) Each Engine Overhaul or major CAM inspection Starter Generator Gearshaft Ball Bearing Propeller Shaft Flanged Annular Ball Bearing On Condition Idler Gearshaft Roller Bearing On Condition Hydraulic Pump, Idler and Fuel Control Drive 9000 Gearshaft Ball Bearing Tachometer Generator and Propeller Governor On Condition Ball Bearing /-5 Rear Propshaft Roller Bearing On Condition Propeller Shaft Annular Ball Bearing On Condition Fuel Control Drive Gear Bearing Set 9000 #Bearing must pass On-Condition inspection. If bearing passes inspection, it is reusable only if the gear involute and M.O.W. inspections are within limits. +Replace only with a new (0 TSN) bearing. Page 18

21 2. H. Periodic Inspection Requirements NOTE: If in conflict with the Engine Maintenance Manual, these inspection interval requirements supersede requirements listed in Table 601 of the Engine Maintenance Manual. The accomplishment of the inspections is described in the Engine Maintenance Manual. Maintain and inspect all accessories and/or electronic components not listed in Tables 2, 2A, 2B, 4, and 7 in accordance with the applicable Engine Maintenance Manual, Chapter , Adjustment/Test, and applicable Inspection/Check and Adjustment/Test section for each accessory/component. Table 2. (TPE331-12B) Periodic Inspection Requirements Inspection Interval Inspection Chapt/Sect/Subj Pre-Flight Air Inlet (Refer to Trouble Shooting, Table 101.) Check for obstructions, evidence of FOD, and for oil leakage from the compressor air/oil seal. Exhaust Pipe (Refer to Trouble Shooting, Table 101.) Check for oil leakage from turbine air-oil seal. First Stage Compressor Impeller Check for evidence of FOD. Daily (Pre-Flight) Oil Level (Refer to Servicing, Table of Contents, procedure to follow.) Must be above ADD mark. Fuel Control Manual Shutoff Lever Cycle shutoff lever and associated linkage to ensure sufficient freedom of operation. Oil Filter Bypass Valve Check for extended indicator pin. Magnetic Chip Detector (Installed) Check for continuity between pin of electrical connector and ground. Every 50 Hours Overspeed Governor (Manual Mode) (Refer to Adjustment/Test, Table of Contents, for paragraph reference and page number of procedure to follow.) Every 100 Hours Spectrometric Oil Analysis Program (SOAP) and Oil Filter (Refer to Inspection/Check, Table of Contents, for paragraph reference and page number of procedure to follow.) (Refer to SB TPE331-A ) Page 19

22 Inspection Interval Every 125 Hours SERVICE BULLETIN Table 2. (TPE331-12B) Periodic Inspection Requirements (Cont) Inspection Chapt/Sect/Subj (Pre SB TPE331-A , , , B-701A/-702A only) Fuel Control P3 Air Filter Remove and clean the filter element. If the filter element is contaminated with oil, clean and inspect the air/oil accumulator system check valves and remove the Fuel Control Unit for internal cleaning. (Post SB TPE331-A , , , B-703A only) Fuel Control P3 Air Filter Remove and clean the filter element. (Post SB TPE331-A , , , B-703A only) Inverted Oil System P3 Air Filter Remove and clean the filter element. (Post SB TPE331-A , B-703A only or Post SB TPE , -12B-701A/-702A only) Filter Screen Remove and clean the filter. (Pre SB TPE331-A , , , B-701A/-702A only) Fuel Control Filtered Orifice Assembly Remove and inspect the orifice assembly. If the orifice assembly is contaminated with oil, clean and inspect the air/oil accumulator system check valves, and remove the Fuel Control Unit for internal cleaning. Magnetic Chip Detector Remove and inspect for chips. Clean or replace with a serviceable unit. Fuel Filter Remove and replace filter element. Fuel Flow Divider and Drain Valve Filter Remove, clean, and inspect, filter element. Fuel Manifold Purge System Filter Remove, clean, and inspect, filter element. Compensating Resistor (Refer to Inspection/Check, Table of Contents, for paragraph reference and page number of procedure to follow.) Test temperature compensation value. Input Gearbox Drain Check to make sure that drain is open. Use air to check drain port passage, as damage to crossover duct could result from the use of hard objects to check passages. Page 20

23 Table 2. (TPE331-12B) Periodic Inspection Requirements (Cont) Inspection Interval Every 250 Hours Inspection Chapt/Sect/Subj Emergency Shutdown (Refer to Inspection/Check, Table of Systems Contents, for paragraph reference and page number of procedure to follow.) Operate airframe emergency feather/fuel shutoff systems to determine if engine feathering valve and fuel shutoff valve have actuated. Plumbing Lines and Connections Check for security, leaks, cracks, cuts, and rubbing. Electrical Wiring and Connections Check for security and damage. Auto Ignition Switch Functional test switch. Controls Linkage Assembly Check for security of locking features. Check for proper alignment of control rod, arms and levers, and for damage. Check bolts and screws securing arms and levers to serrated shaft. Lubricate rod end bearings if binding is noted. Igniter Plugs Remove, clean and inspect. Fuel Manifold and Nozzle (Refer to NOTE 1.) Assembly Fuel Control/Fuel Pump Integrity (Refer to Inspection/Check, Table of Contents, for paragraph reference and page number of procedure to follow.) NTS Ground Check (Refer to Adjustment/Test, Table of Contents, for paragraph reference and page number of inspection procedure to follow.) Check operation of NTS system. This check shall be performed every 250 hours operating time, and any time maintenance is performed on torque sensing or NTS system components. Plenum Drain Valves Check operation of plenum drain valves without removing from engine as follows: With engine not operating, plenum drain valves should be open. Open position may be assured if air passes freely through valve when slight air pressure is applied at the attached drain tubes. Engine Oil (Type I) (Refer to Servicing, Table of Contents, procedure to follow.) Drain and refill with new oil. Page 21

24 Table 2. (TPE331-12B) Periodic Inspection Requirements (Cont) Inspection Interval Inspection Chapt/Sect/Subj Every 500 Hours Plenum Drain Valves Remove and test for opening and closing. Engine Oil (Type II) (Refer to Servicing, Table of Contents, procedure to follow.) Drain and refill with new oil. Every 1000 Hours (Pre SB TPE ) Torque Load Arm (Refer to Inspection/Check, Table of Contents, for paragraph reference and page number of procedure to follow.) Applied torque inspection. Starter-Generator Drive Gearshaft Insert (Splined Adapter) Inspect for wear at EVERY access. Every 1400 to 1600 Hours Every 2900 to 3100 Hours NOTE 1. Compressor Air/Oil Seal and Rotor Gearbox Turbine (Hot) Section Overhaul Engine (Refer to Inspection/Check, Table of Contents, for paragraph reference and page number of procedure to follow.) (Refer to SB TPE331-A ) (Refer to Inspection/Check, Table of Contents, for paragraph reference and page number of procedure to follow.) Refer to Paragraph 2.I. of this service bulletin. Refer to SB TPE331-A Fuel nozzle assembly inspections may be accomplished in conjunction with an airframe inspection, but do not exceed inspection interval listed. Fuel nozzle assemblies must be replaced with new or cleaned fuel nozzle assemblies every 250 operating hours. Perform hot gas path inspection (borescope inspection) following detection of secondary nozzle plugging, which exceeds 20% of total secondary flow, or two plugged nozzles. Page 22

25 Table 2A. (TPE331-12JR, TPE331-12UA/-12UAR/-12UHR-701G) Periodic Inspection Requirements Inspection Interval Inspection Chapt/Sect/Subj Pre-Flight Air Inlet (Refer to Trouble Shooting, Table 101.) Revision 27, Sept 17/03 Check for obstructions, evidence of FOD, and for oil leakage from compressor air-oil seal. Exhaust Pipe (Refer to Trouble Shooting, Table 101.) Check for oil leakage from turbine air-oil seal. First Stage Compressor Impeller Check for evidence of FOD. Daily (Pre-Flight) Oil Level (Refer to Servicing, Table of Contents, for paragraph reference and page number of procedure to follow.) Must be above ADD mark. (TPE331-12UA/ -12UAR/-12UHR -701G) Every 100 Hours (TPE331-12JR) Every 150 Hours Spectrometric Oil Analysis Program (SOAP) and Oil Filter Oil Filter (Refer to Inspection/Check, Table of Contents, procedure to follow.) (Refer to SB TPE331-A ) (Refer to Inspection/Check, Table of Contents, procedure to follow.) Inspection should be accomplished in conjunction with an airframe inspection, but do not exceed 155 hours. Every 150 Hours Fuel Filter Remove and replace filter element. Compensating Resistor (Refer to Inspection/Check, Table of Contents, procedure to follow.) Test temperature compensation value. Input Gearbox Drain Check to make sure that drain is open. Use air to check drain port passage, as damage to crossover duct could result from the use of hard objects to check passages. Every 200 Hours Emergency Shutdown Systems (Refer to Inspection/Check,Table of Contents, procedure to follow.) Operate airframe emergency feather/fuel shutoff systems to determine if engine feathering valve and fuel shutoff valve have actuated. First Stage Compressor Impeller Check for evidence of FOD. Page 23

26 Inspection Interval Revision 27, Sept 17/03 Table 2A. (TPE331-12JR, TPE331-12UA/-12UAR/-12UHR-701G) Periodic Inspection Requirements (Cont) Inspection Chapt/Sect/Subj Every 300 Hours Overspeed Governor (Refer to Adjustment/Test, Table of Contents, procedure to follow.) Operational check. NTS System Ground Check (Refer to Adjustment/Test, Table of Contents, procedure to follow.) Check operation of NTS system. This check shall be performed every 300 hours operating time, and any time maintenance is performed on torque sensing or NTS system components. Fuel Manifold Purge System Filter Remove and clean filter element. Plumbing Lines and Connections Check for security, leaks, cracks, cuts, and rubbing. Electrical Wiring and Connections Check for security and damage. Magnetic Drain Plug (Chip Detector) Remove and inspect. For two piece unit, remove knurled plug and accomplish visual inspection. Controls Linkage Assembly Check for security of locking features. Check for proper alignment of control rod, arms and levers, and for damage. Check bolts and screws securing arms and levers to serrated shaft. Lubricate rod end bearings if binding is noted. Auto Ignition Switch Functional test switch. Igniter Plugs Remove, clean and inspect. Plenum Drain Valves Check operation of plenum drain valves without removing from engine as follows: With engine not operating, plenum drain valves should be open. Open position may be assured if air passes freely through valve when slight air pressure is applied at the attached drain tubes. Fuel Flow Divider Valve Filter Remove, clean and inspect filter element. Page 24

27 Table 2A. (TPE331-12JR, TPE331-12UA/-12UAR/-12UHR-701G) Periodic Inspection Requirements (Cont) Inspection Interval Inspection Chapt/Sect/Subj Every 300 Hours Torque Limiter Bypass Valve Filter Remove and clean. Every 400 Hours Engine Oil Change (Type I) (Refer to Servicing, Table of Contents, for paragraph reference and page number of procedure to follow.) Drain and refill with new oil. Every 450 Hours Fuel Manifold and (Refer to NOTE 1.) Nozzle Assemblies Every 600 Hours Plenum Drain Valves Remove and test for opening and closing. Every 900 Hours Engine Oil Change (Type II) (Refer to Servicing, Table of Contents, for paragraph reference and page number of procedure to follow.) Drain and refill with new oil. Every 1000 Hours (Pre SB TPE ) Torque Load Arm (Refer to Inspection/Check, Table of Contents, procedure to follow.) Applied torque inspection. Every 1400 to Compressor Air/Oil Hours for Seal and Rotor 3000 Hour TBO Turbine (Hot) Section (Refer to Inspection/Check, Table of Contents, procedure to follow.) Gearbox (Refer to Inspection/Check, Table of Contents, procedure to follow.) (Refer to SB TPE331-A and TPE331-A ) Every 2400 to Compressor Air/Oil Seal Hours for and Rotor 5000 Hour TBO Turbine (Hot) Section (Refer to Inspection/Check, Table of Contents, procedure to follow.) Gearbox (Refer to Inspection/Check, Table of Contents, procedure to follow.) (Refer to SB TPE331-A and TPE331-A ) Propeller Pitch Control Cam Assembly Inspect after disassembly in accordance with the Engine Maintenance Manual. Revision 27, Sept 17/03 Page 25

28 Inspection Interval Every 2900 to 3100 Hours Every 3400 to 3600 Hours for 7000 Hour TBO or CAM Inspection with Gearbox Inspection Every 3400 to 3600 Hours for 7000 Hour TBO or CAM Inspection without Gearbox Inspection No later than 3700 Hours Every 3700 (Spline) Hours Maximum Every 4900 to 5100 Hours Every 6900 to 7100 Hours Table 2A. (TPE331-12JR, TPE331-12UA/-12UAR/-12UHR-701G) Periodic Inspection Requirements (Cont) Inspection Chapt/Sect/Subj Overhaul Engine Refer to Paragraph 2.I. of this service bulletin. Refer to SB TPE331-A and TPE331-A Compressor Air/Oil Seal and Rotor Turbine (Hot) Section (Refer to Inspection/Check, Table of Contents, procedure to follow.) Gearbox (Refer to Inspection/Check, Table of Contents, procedure to follow.) (Refer to SB TPE331-A and TPE331-A ) Propeller Pitch Control Cam Assembly Inspect after disassembly in accordance with the Engine Maintenance Manual. Turbine (Hot) Section (Refer to Inspection/Check, Table of Contents, procedure to follow.) Gearbox Refer to SB TPE331-A and TPE331-A Propeller Pitch Control Cam Assembly Inspect after disassembly in accordance with the Engine Maintenance Manual. Fuel Control/Fuel Pump Integrity Fuel Control/Fuel Pump Mating Spline Overhaul Engine Overhaul Engine or accomplish CAM inspection (Refer to Inspection/Check, Table of Contents, procedure to follow.) (Refer to Inspection/Check, Table of Contents, procedure to follow.) (Refer to NOTE 2.) Refer to Paragraph 2.I. of this service bulletin. Refer to SB TPE331-A and TPE331-A Refer to Paragraph 2.J. of this service bulletin. Refer to SB TPE331-A and TPE331-A Revision 27, Sept 17/03 Page 26

29 Inspection Interval Table 2A. (TPE331-12JR, TPE331-12UA/-12UAR/-12UHR-701G) Periodic Inspection Requirements (Cont) Inspection Chapt/Sect/Subj Annually Magnesium Housing (Nose Cone Assembly) (In conjunction Corrosion (Accessory Drive Housing) with an airframe annual inspection or an equivalent aircraft inspection.) NOTE 1. NOTE 2. Inspect exposed painted surfaces for missing, peeling, cracked, blistered, crinkled or scratched paint. Repair areas that have missing, peeling, cracked, blistered, crinkled or scratched paint. There is no limit to the size or number of defective or damaged paint areas which may be repaired provided that any corrosion present has penetrated less than inch. If corrosion has penetrated inch or more, refer to appropriate section for inspection limits. Repair in accordance with , Cleaning/Painting, Repair of Defective or Damaged Paint and Minor Corrosion on Magnesium Components. Fuel nozzle assembly inspections may be accomplished in conjunction with an airframe inspection, but do not exceed inspection interval listed. Fuel nozzle assemblies must be replaced with new or cleaned fuel nozzle assemblies every 450 operating hours. Perform hot gas path inspection (borescope inspection) following detection of secondary nozzle plugging, which exceeds 20% of total secondary flow, or two plugged nozzles. All Fuel Pumps installed with Fuel Control Units EXCEPT Fuel Control Units, Part No /-2/-3. Inspect Fuel Pump and Fuel Control Unit splines at the periodic 3700 hour interval. Inspect replacement Fuel Pump and Fuel Control Unit splines at time of replacement of either Fuel Pump or Fuel Control Unit. (Spline inspection of new or newly overhauled component not required.) Inspect Fuel Pump splines when replacement Fuel Control Unit is installed. (Spline inspection of new or newly overhauled Fuel Pump not required.) Inspect Fuel Control splines when replacement Fuel Pump is installed. (Spline inspection of new or newly overhauled Fuel Control not required.) All Fuel Pumps installed with Fuel Control Units, Part No /-2/-3. Inspect Fuel Pump splines at time of installation of Fuel Control Unit. Inspect Fuel Pump splines when replacement Fuel Pump is installed. (Spline inspection of new or newly overhauled Fuel Pump not required.) Revision 27, Sept 17/03 Page 27

30 Table 2B. (TPE331-12UA/-12UAR/-12UHR-701H through -708H) Periodic Inspection Requirements Inspection Interval Inspection Chapt/Sect/Subj Pre-Flight Air Inlet (Refer to Trouble Shooting, Table 101.) Check for obstructions, evidence of FOD, and for oil leakage from compressor air-oil seal. Exhaust Pipe (Refer to Trouble Shooting, Table 101.) Check for oil leakage from turbine air-oil seal. Daily (Pre-Flight) Oil Level (Refer to Servicing, Table of Contents, for paragraph reference and page number of procedure to follow.) Must be above ADD mark. Every 100 Hours Spectrometric Oil Analysis Program (SOAP) and Oil Filter (Refer to Inspection/Check, Table of Contents, procedure to follow.) (Refer to SB TPE331-A ) Every 200 Hours Emergency Shutdown Systems (Refer to Inspection/Check, Table of Contents, procedure to follow.) Operate airframe emergency feather/fuel shutoff systems to determine if engine feathering valve and fuel shutoff valve have actuated. Fuel Filter (Aircraft without a Fuel Filter By-pass Light) Remove and replace with a new filter element. Input Gearbox Drain Check to make sure that drain is open. Use air to check drain port passage, as damage to crossover duct could result from the use of hard objects to check passages. Compensating Resistor (Refer to Inspection/Check, Table of Contents, procedure to follow.) Test temperature compensation value. Page 28

31 Inspection Interval Table 2B. (TPE331-12UA/-12UAR/-12UHR-701H through -708H) Periodic Inspection Requirements (Cont) Inspection Chapt/Sect/Subj Every 200 Hours First Stage Compressor Impeller Check for evidence of FOD. Every 300 Hours Overspeed Governor (Refer to Adjustment/Test, Table of Contents, procedure to follow.) Operational check. Every 400 Hours NTS System Ground Check (Refer to Adjustment/Test, Table of Contents, procedure to follow.) Check operation of NTS system. This check must be performed every 300 hours operating time, and any time maintenance is performed on torque sensing or NTS system components. Fuel Filter (Aircraft with a Fuel Filter By-pass Light) Remove and replace with a new filter element. Controls Linkage Assembly Check for security of locking features. Check for proper alignment of control rod, arms and levers, and for damage. Check bolts and screws securing arms and levers to serrated shaft. Lubricate rod end bearings if binding is noted. Plumbing Lines and Connections Check for security, leaks, cracks, cuts, and rubbing. Fuel Manifold Purge System Filter Remove, clean, and inspect, filter element. Electrical Wiring and Connections Check for security and damage. Magnetic Drain Plug (Chip Detector) Remove and inspect. For two piece unit, remove knurled plug and accomplish visual inspection. Page 29