2900 Selma Highway Montgomery, AL 36108 USA Tel: 334-386-5400 Fax: 334-386-5450 201F Fuel Pump Valve Assembly Leakage 1. Planning Information A. Effectivity (1) Hartzell Engine Technologies LLC (HET) 201F Series fuel pump with part numbers as used on Lycoming engines listed in Table 1 of this service bulletin. a. Fuel pumps with serial numbers H-PBNxxxFP through H-QINxxxFP are affected. These fuel pumps were manufactured between February 2012 and September 2013. b. An affected fuel pump may be new, rebuilt, or overhauled. (2) All valve assemblies P/N 063F-5001 sold as replacement parts between February 2012 and September 2013 are affected by this Service Bulletin. a. Any 201F fuel pump utilizing an affected P/N 063F-5001 valve assembly in a field repair or overhaul. CAUTION: DO NOT USE OBSOLETE OR OUTDATED INFORMATION. PERFORM ALL INSPECTIONS OR WORK IN ACCORDANCE WITH THE MOST RECENT REVISION OF THE APPLICABLE AIRCRAFT AND/OR ENGINE MAINTENANCE MANUAL (MM) AND THIS SERVICE BULLETIN (SB). INFORMATION CONTAINED IN THE MM AND THE SB MAY BE SIGNIFICANTLY CHANGED FROM EARLIER REVISIONS. USE OF OBSOLETE INFORMATION MAY CREATE AN UNSAFE CONDITION THAT MAY RESULT IN DEATH, SERIOUS BODILY INJURY, AND/OR SUBSTANTIAL PROPERTY DAMAGE. REFER TO THE APPLICABLE MM INDEX AND THE HET WEBSITE FOR THE MOST RECENT REVISION LEVELS. B. Concurrent Requirements (1) Compliance with the most current revision of HET SB 041 and SB 045. C. Reason (1) Fuel leaks at the fuel pump valve assembly have been observed. These leaks may be due to assembly issues associated with the valve assembly. (2) Should fuel leak at the valve assembly, it will exit the pump at the vent drain port in the relief valve cover. Depending upon the installation, fuel may be vented into the aircraft overboard drain system, vented into the turbocharger reference line, or vented into the engine compartment. (3) Some overboard fuel drain systems may connect the pump housing drain port with the relief valve cover vent drain port. This requires that the pump housing drain port be checked for fuel leakage as well to identify the fuel leak path. (4) Fuel pump valve assembly leakage may pose a fire hazard should fuel enter the engine compartment. (5) Regulatory action is unknown. Rev. New: December 12/13 SB 056 2013 - Hartzell Engine Technologies. - All rights reserved Page 1 of 10
D. Description (1) This Service Bulletin provides Instructions for Continued Airworthiness (ICA). (2) This Service Bulletin is being issued to require a recurring inspection to detect fuel leakage past the fuel pump valve assembly at the relief valve cover vent drain port and at the pump housing drain port. E. Compliance (1) If the fuel pump has been identified as affected by this Service Bulletin per 1.A or 3.A: a. At the next fifty (50) hours time in service (TIS) or annual inspection whichever comes first, perform a fuel leak inspection at the relief valve cover vent drain port and at the seal drain port in the pump housing in accordance with the Accomplishment Instructions of this Service Bulletin. b. If a leak IS NOT found, the unit may remain in service with recurrent 50 hour/annual TIS inspection (first to occur) per this Service Bulletin. c. If a leak IS found perform the Terminating Action in accordance with the Accomplishment Instructions. d. If an affected 201F fuel pump is found in inventory, return it to HET in accordance with Corrective Action 3.C(1) of this Service Bulletin. (2) Replacement Valve assemblies, P/N 063F-5001 in inventory that were sold by HET between February 2012 and September 2013, must be returned to HET in accordance with Corrective Action 3.C(1) of this Service Bulletin. (3) Replacement and return of the valve assembly (P/N 063F-5001) or fuel pump with an unaffected fuel pump or valve assembly and the return of affected unused valve assemblies are the terminating action for this Service Bulletin. F. Approval (1) FAA acceptance has been obtained on technical data in this publication that affects type design. G. Manpower (1) Negligible if performed in conjunction with regularly scheduled maintenance inspection as required by the engine/aircraft manufacturer. H. References (1) Applicable aircraft POH/AFM. (2) Aircraft maintenance manual (as applicable). (3) Lycoming engine Service Instructions or maintenance manual (for applicable model). I. Other Publications Affected (1) None J. Weight and Balance (1) Not affected SB 056 Rev. New: December 12/13 Page 2 of 10 2013 - Hartzell Engine Technologies. - All rights reserved
2. Material Information (As applicable to engine application.) A. If being replaced, one (1) each, 201F fuel pump of same P/N being replaced but not affected by this Service Bulletin.* B. If being repaired, one (1) each, valve assembly P/N 063F-5001. * If the fuel pump is being replaced, remember to remove and retain the fittings. These parts are provided by the airframe or engine manufacturer. 3. Accomplishment Instructions WARNING: THIS PROCEDURE MUST BE PERFORMED BY COMPETENT AND QUALIFIED PERSONNEL WHO ARE FAMILIAR WITH ENGINE AND AIRFRAME MAINTENANCE THAT IS SPECIFIC TO THE ENGINE FUEL SYSTEM. FAILURE TO DO SO MAY RESULT IN ECONOMIC LOSS, EQUIPMENT DAMAGE, AND/OR PHYSICAL INJURY. CAUTION 1: DO NOT USE OBSOLETE OR OUTDATED INFORMATION. PERFORM ALL INSPECTIONS OR WORK IN ACCORDANCE WITH THE MOST RECENT REVISION OF THIS SERVICE BULLETIN AND THE APPLICABLE AIRCRAFT, ENGINE AND/OR HET 200201-0000 MAINTENANCE MANUAL. INFORMATION CONTAINED IN THESE MANUALS OR THIS SERVICE BULLETIN MAY BE SIGNIFICANTLY CHANGED FROM EARLIER REVISIONS. FAILURE TO COMPLY WITH THE SERVICE BULLETIN OR THE USE OF OBSOLETE INFORMATION MAY CREATE AN UNSAFE CONDITION THAT MAY RESULT IN DEATH, SERIOUS BODILY INJURY, AND/OR SUBSTANTIAL PROPERTY DAMAGE. REFER TO THE HET WEBSITE FOR THE MOST RECENT REVISION OF THE 200201-0000 MANUAL. CAUTION 2: DO NOT DEPEND ON THIS SERVICE BULLETIN FOR GAINING ACCESS TO THE AIRCRAFT OR ENGINE. ACCESS REQUIRES THE USE OF THE APPLICABLE MANUFACTURER'S MAINTENANCE MANUALS OR SERVICE INSTRUCTIONS. IN ADDITION, ANY PREFLIGHT OR IN FLIGHT OPERATIONAL CHECKS REQUIRE USE OF THE APPROPRIATE AFM OR POH. A. Fuel Pump Identification Service Bulletin (1) If positive identification of the fuel pump and manufacture date can be made through the engine or aircraft paperwork, continue but skip step 5. a. Affected P/N 063F-5001 replacement valve assemblies that were placed in service at overhaul or repair must be identified using the engine or aircraft paperwork. b. Any part number or serial number 201F fuel pump is affected if an affected valve assembly P/N 063F-5001 has been installed. (2) If positive identification cannot be made, continue with this instruction. Refer to Figure 1 for the serial number breakdown. (3) Access the aircraft engine driven fuel pump in accordance with the applicable engine service instructions and/or aircraft maintenance manual. Rev. New: December 12/13 SB 056 2013 - Hartzell Engine Technologies. - All rights reserved Page 3 of 10
NOTE: (4) Remove the cowling from the engine and locate the fuel pump on the particular model engine you are inspecting. (5) Locate the data tag on the fuel pump to identify if the unit is an HET 201F fuel pump. Record the serial number and use the serial number breakdown shown in Figure 1 to determine the manufacture date. a. If the unit IS NOT an affected HET 201F fuel pump, proceed to section 3.D(4) for Return to Service. b. If the unit IS an affected HET 201F fuel pump, proceed to 3.B. B. Fuel Leak Inspection Service Bulletin An existing fuel leak may be noticed as a blue or blue green stain in the vicinity of or dripping from the overboard drain line. Any fuel leakage noticed regardless of reason, fuel pump make, model, or manufacturer should be investigated for cause. If auto gas is being used, no stains may be apparent. In such cases, leak detection must be visually observed as liquid at the overboard fuel drain or in the applicable fuel pump port. CAUTION: WHEN HANDLING FUEL, USE ALL PRECAUTIONS NECESSARY TO CONTAIN ANY SPILLED OR LEAKED FUEL AND LIMIT ACCESS TO ANYONE NOT ASSIGNED THE TASK OF THE TEST PROCEDURES HEREIN. DO NOT LOCATE THE AIRCRAFT BEING TESTED NEAR OPEN FLAME, HEAT SOURCES, ELECTRICAL SPARKS OR OTHER IGNITION SOURCES. FAILURE TO FOLLOW THESE PRECAUTIONS MAY CREATE AN UNSAFE CONDITION THAT MAY RESULT IN DEATH, SERIOUS BODILY INJURY, AND/OR SUBSTANTIAL PROPERTY DAMAGE. (1) Inspect the 201F fuel pump for fuel leakage at the vent drain port in the relief valve cover and at the pump housing drain. The pump housing seal drain will be connected to the aircraft overboard fuel drain system. The relief valve cover vent drain port may be vented to the cowl area by means of an orificed plug (refer to figure 2), connected to an aircraft overboard drain (refer to Figure 3), or in turbocharged applications connected to an induction system air reference line (refer to Figure 4). (2) Disconnect the overboard drain line from the fuel pump relief valve cover vent drain fitting. (refer to Figure 2). Place a protective cap over the disconnected line. (3) Remove and retain the fitting from the fuel pump relief valve cover vent drain port. If this fitting is connected to a drain or reference line/hose, disconnect from the fitting and place a protective cap over the disconnected line. (4) In a secure area utilizing instructions in the applicable AFM, POH and/or aircraft maintenance manual, turn on the aircraft electrical power, set fuel selector to fullest tank and place mixture at idle cut off. Turn on the aircraft boost or auxiliary fuel pump and check for a positive fuel pressure gauge indication. (5) Allow boost or auxiliary pump to operate for at least two minutes. Visually inspect for fuel leaks at the fuel pump relief valve cover vent drain port and the seal drain locations. SB 056 Rev. New: December 12/13 Page 4 of 10 2013 - Hartzell Engine Technologies. - All rights reserved
(6) Following instructions in the applicable AFM/POH and/or aircraft maintenance manual, turn off boost or auxiliary fuel pump, set fuel selector to off position and turn off aircraft electrical power. (7) If a leak IS found, proceed to 3.C. (8) If leakage IS NOT found, continued operation of the aircraft is permissible in accordance with the provisions given in Compliance. To make the fuel pump operational, continue with this instruction step then proceed to 3.D(2) Return to Service. a. If an orifice plug was installed in the relief valve cover drain port, clean the vent drain port threads with isopropyl alcohol and install the orifice plug. Torque to 30-40 inch pounds. (3.39-4.52 Nm) b. If an overboard drain line fitting was installed in the relief valve cover drain port, clean the vent drain port fitting threads with isopropyl alcohol, remove cap, and reconnect the drain line/hose. Torque to the value listed in the engine or aircraft manufacturers service instructions or manuals. c. If a turbocharger reference line was connected to the relief valve cover drain port, clean the vent drain port fitting threads with isopropyl alcohol. Remove cap and reconnect the turbocharger reference line/hose. Torque to the value listed in the engine or aircraft manufacturers service instructions or manuals. C. Corrective Action: Service Bulletin (1) Remove the fuel pump from the engine for repair or replacement in accordance with current engine/airframe maintenance manual or service instructions. (2) If the pump is to replaced, retain all engine or airframe supplied fittings for installation in the replacement fuel pump. (3) If repairing the 201F fuel pump, the 063F-5001 valve assembly must be replaced with new unaffected valve assembly. a. Repair by replacement of the valve assembly or any other repair must be done in accordance to the latest revision of the HET P/N 200201-0000 Overhaul & Maintenance manual. Rev. New: December 12/13 SB 056 2013 - Hartzell Engine Technologies. - All rights reserved Page 5 of 10
D. Return to Service (1) Install the replacement or repaired 201F fuel pump on the aircraft engine as prescribed in the latest revision of the aircraft or engine maintenance manual or service instructions. (2) Perform the recommended fuel pump functional tests in accordance with the appropriate aircraft maintenance manual, engine service instructions, and per operational test in the AFM or POH. (3) Using the applicable aircraft and engine manufacturer's maintenance manuals of the latest revision, install any portion of the aircraft that was removed to gain access. (4) The aircraft may be returned to service after making a logbook entry to indicate completion of this Service Bulletin as applicable: (a) (b) Inspection noting the recurring TIS limitation in 1.E(1). Terminating Action by replacement or repair of the applicable 201F fuel pump. 4. Contact Information A. All communications regarding this Service Bulletin must be placed either through Hartzell Engine Technologies Product Support at +1.334.386.5400 or at +1.334.386.5441. If via Fax +1.334.386.5450. B. Written communications must be placed through Hartzell Engine Technologies Product Support, 2900 Selma Highway, Montgomery, AL 36108, USA. C. If e-mail communication is desired, use techsupport@hartzellenginetech.com. For a copy of this service bulletin, go to Hartzell Engine Technologies website:http://www.hartzellenginetech.com and follow instructions or use. D. If returning an inventory fuel pump or valve assembly, normal warranty procedures apply. SB 056 Rev. New: December 12/13 Page 6 of 10 2013 - Hartzell Engine Technologies. - All rights reserved
HET H- P B N xxx FP R Year Code Month Code Factory Code (no user info) 3-Digit Serial Number Fuel Pump (component type) Rebuilt /Overhauled Year Code Month Code Serial Number P = 2012, Q = 2013, R = 2014, etc. A = January, B = February, C = March, etc. 3-Digit Sequential Number Examples: Production: Factory Rebuilt: Part Number: 201F-5008 201F-5008R Serial Number: H-PBNxxxFP H-PBNxxxFPR Date of Mfg.: February, 2012 February, 2012 Figure 1-201F Serial Number Breakdown Orifice Plug in Vent Drain Port of the Relief Valve Cover (other fitting types may be found) Overboard Drain Port with Typical Fitting Figure 2 - Typical 201F Fuel Pump with Orifice Plug Rev. New: December 12/13 SB 056 2013 - Hartzell Engine Technologies. - All rights reserved Page 7 of 10
Typical 201F Fuel Pump Vent drain Port Line/Hose with Typical Fitting Figure 3 - Typical 201F Fuel Pump Vent drain Port to Overboard Drain System Typical 201F Fuel Pump Vent drain Port with Typical Fitting Turbocharger Reference Line /Hose. Figure 4 - Typical 201F Fuel Pump Vent drain Port with Turbocharger Reference Line/Hose SB 056 Rev. New: December 12/13 Page 8 of 10 2013 - Hartzell Engine Technologies. - All rights reserved
Table 1 - Cross Reference* * This Service Bulletin addresses products for which HET holds FAA PMA approval. Your aircraft or engine may have a similar HET manufactured product that has been installed under an aircraft or engine manufacturers authority whose part numbers may not be listed in this table. Rev. New: December 12/13 SB 056 2013 - Hartzell Engine Technologies. - All rights reserved Page 9 of 10
Intentionally Left Blank SB 056 Rev. New: December 12/13 Page 10 of 10 2013 - Hartzell Engine Technologies. - All rights reserved
APPENDIX I COMMERCIAL ASSISTANCE: In addition to warranty coverage provided by the HET Limited Warranty, HET will provide additional commercial assistance to comply with SB 056 under the terms outlined in this Appendix. Commercial Assistance: HET Limited Warranty Policy terms and conditions apply. In addition, the following will be provided with the submission of a completed PPCR (Attachment A) along with copies of invoices showing breakdown of labor charges and log book entries. This will serve as a claim form for the commercial assistance. Any commercial assistance shall terminate one (1) year from the date of this service bulletin. Identification: Labor is negligible. Removal and Installation: (includes gaining access) No labor - to be performed in conjunction with normal inspection and maintenance. Leak Test (repetitive) Repair by Valve Ass y Material (one only) No labor - to be performed in conjunction with normal inspection and maintenance. Up to one half (0.5) hour labor (up to $37.50 maximum) per engine for repair only. This assistance is for affected HET 201F fuel pump using P/N 063F-5001 Valve Ass y. (When performed in conjunction with normal inspection and maintenance.) One (1) ea. 201F Fuel Pump of the applicable P/N per the HET limited new parts warranty. - OR - For repair only, one (1) ea. Valve Ass y P/N 063F-5001 per the HET limited new parts warranty. Parts in inventory Refer to the HET limited new parts warranty terms and conditions. WARRANTY STATEMENT: A. The sole warranty for the actions within this Service Bulletin are contained in the HET Limited Warranty Policy issued with the purchase of each new or rebuilt 201F Fuel Pump (see terms and conditions therein). B. Commercial assistance may apply as stated in Appendix I. Attachment A of this Service Bulletin is required. C. Issuance of this Service Bulletin in no way constitutes an implied or expressed warranty of any kind. D. This publication does not imply or state any responsibility for the workmanship of any person or entity performing work or maintenance on the engine or aircraft fuel system. SHIPPING INFORMATION: HET Limited Warranty Policy terms and conditions apply. File a claim for warranty consideration and return affected parts through place of purchase using the methods prescribed for shipping. CONTACT INFORMATION: All communications regarding this service bulletin, must be placed either through Hartzell Engine Technologies Product Support at +1.334.386.5441, or via Fax +1.334.386.5450. All telephone communications outside North America use +1 334 386 5441. Written communications must be placed through Hartzell Engine Technologies Product Support, 2900 Selma Highway, Montgomery, AL 36108, USA. If e-mail communication is desired, go to our website: http://www.hartzellenginetech.com and select contact and follow the instructions or use techsupport@hartzellenginetech.com. Rev. New: December 12/13 SB 056 2013 - Hartzell Engine Technologies. - All rights reserved Appendix 1
ATTACHMENT A - SB 056 SECTION I: Customer information (Completed by End User) PPCR Publication Product Condition Report (To validate warranty or commercial assistance, all information MUST be filled out.) Name: Date of Report: Tel: Company Name: E-mail: Address: Aircraft Mfg/: Time in Service: Model: S/N: Engine (as may be applicable) SECTION II: Product or Component Information (Completed by End User) Nomenclature: Fuel Pump, 201F or Valve Ass y (circle one) Serial Number: Part Number: Batch/Date Code: Part Time in Service: SECTION III: Compliance Information: (Completed by Repair Facility) Compliance with SB-056: YES Fuel Pump Leaks: YES NO Fuel Pump Replaced: YES NO Fuel Pump Repaired: YES NO If yes, please describe condition and leak location: Eligibility: To be eligible for any commercial assistance, this form must be completed as instructed above and will serve as a claim form. NO reimbursement will be made without completing this form. Any commercial assistance shall terminate one (1) year from the date of this service bulletin. For further information contact Hartzell Engine Technologies LLC at: 2900 Selma Highway, Montgomery, AL, USA or FAX to HET Customer Service, +1.334.386.5450. The complete service bulletin is available to you online via our website at http://www.hartzellenginetech.com. Rev. New: 12/12/13