2000-22-51 FIREFLY AVIATION HELICOPTER SERVICES (PREVIOUSLY ERICKSON AIR-CRANE CO.); GARLICK HELICOPTERS, INC.; HAWKINS AND POWERS AVIATION, INC.; INTERNATIONAL HELICOPTERS, INC.; TAMARACK HELICOPTERS, INC. (PREVIOUSLY RANGER HELICOPTER SERVICES, INC.); ROBINSON AIR CRANE, INC.; WILLIAMS HELICOPTER CORPORATION (PREVIOUSLY SCOTT PAPER CO.); SMITH HELICOPTERS; SOUTHERN HELICOPTER, INC.; SOUTHWEST FLORIDA AVIATION; ARROW FALCON EXPORTERS, INC. (PREVIOUSLY UTAH STATE UNIVERSITY); U.S. HELICOPTER, INC.; and WESTERN INTERNATIONAL AVIATION, INC.: Amendment 39-12034. Docket No. 2000-SW-42-AD. Supersedes Emergency AD 2000-08-53, Docket No. 2000-SW-08-AD and AD 89-17-03, Amendment 39-6251, Docket No. 88-ASW-33. \n\n\tApplicability: Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P; and Southwest Florida Aviation SW204, SW204HP, SW205, and SW205A-1 helicopters, manufactured by Bell Helicopter Textron Inc. (BHTI) for the Armed Forces of the United States, with main rotor mast (mast), part number (P/N) 204-011-450-007, -105, or -109, or main rotor trunnion (trunnion), P/N 204-011-105-001, installed, certificated in any category. \n\n\tNOTE 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tNOTE 2: This AD requires using new factors to recalculate the FACTORED flight hours and the accumulated Retirement Index Number (RIN) for masts installed on certain helicopter models. This AD also expands the serial number (S/N) applicability for the one-time special inspection of the mast. \n\n\tTo prevent failure of a mast or trunnion, separation of the main rotor system, and subsequent loss of control of the helicopter, accomplish the following: \n\n\t(a) For the mast, P/N 204-011-450-007, -105, or -109: \n\n\tNOTE 3: The next higher assembly level for the affected P/N's are the 204-040-366 mast assemblies. Check the aircraft records for the appropriate P/N and assembly level. \n\n\t\t(1) Within 10 hours time-in-service (TIS), create a component history card or equivalent record for the mast. \n\n\t\t(2) Within 10 hours TIS, determine and record the accumulated RIN and revised hours TIS for the mast as follows: \n\n\t\t\t(i) Review the aircraft maintenance records for the mast. If thehelicopter model installation history or hours TIS of the mast is unknown, remove the mast from service, identify the mast as unairworthy, and replace it with an airworthy mast before further flight. \n\n\t\t\t(ii) Determine the accumulated RIN and the revised hours TIS in accordance with the Instructions in Appendix 1. For those hours TIS the mast has been installed on a BHTI Model 204B, 205A, 205A-1, 205B, or 212 helicopter, determine the accumulated RIN in accordance with the AD's issued for those helicopters. \n\n\t\t\t(iii) Record the accumulated RIN and revised hours TIS for the mast on the component history card or equivalent record. Use the revised hours TIS as the new hours TIS for the mast. \n\n\t\t(3) Before further flight after accomplishing the requirements of paragraph (2), remove from service any mast that has accumulated 265,000 or more RIN or 15,000 or more revised hours TIS and identify the mast as unairworthy. Replace the mast with an airworthy mast. \n\n\t\t(4) Within25 hours TIS, remove any hub spring installed on any affected helicopter. \n\n\tNOTE 4: U. S. Army Modification Work Order (MWO) 55-1520-242-50-1 pertains to the removal of the hub spring and replacement of any required parts. U.S. Army Safety of Flight Message UH-1-00-10 dated July 19, 2000, also pertains to the subject of this AD. \n\n\t\t(5) Determine whether a mast with S/N 00000 through 52720, 61433 through 61444, or 61457 through 61465 (regardless of prefix), has ever been installed on a helicopter while operated with a hub spring. \n\n\t\t\t(i) If a mast has never been installed on a helicopter while operated with a hub spring, before reaching 100,000 RIN, inspect the upper and lower snap ring grooves in the damper clamp splined area for: \n\n\t\t\t\t(A) A minimum radius of 0.020 inch around the entire circumference (see Figures 1 and 2), using a 100x or higher magnification. If any snap ring groove radius is less than 0.020 inch, identify the mast as unairworthy and replace it withan airworthy mast before exceeding 100,000 RIN. \n\n\t\t\t\t(B) A burr (see Figures 1 through 3), using a 200x or higher magnification. If a burr is found in any snap ring groove/spline intersection, identify the mast as unairworthy and replace it with an airworthy mast before exceeding 170,000 RIN. \n\n\t\t\t(ii) If a mast has ever been installed on a helicopter while operated with a hub spring or if the history of a hub spring installation is unknown, before reaching 100,000 RIN or 400 unfactored flight hours, whichever occurs first, inspect the upper and lower snap ring grooves in the damper clamp splined area for: \n\n\t\t\t\t(A) A minimum radius of 0.020 inch around the entire circumference (see Figures 1 and 2), using a 100x or higher magnification. If any snap ring groove radius is less than 0.020 inch, identify the mast as unairworthy and replace it with an airworthy mast before further flight. \n\n\t\t\t\t(B) A burr (see Figures 1 through 3), using a 200x or higher magnification. Ifa burr is found in any snap ring groove/spline intersection, identify the mast as unairworthy and replace it with an airworthy mast before further flight. \n\n\t\t(6) After accomplishing the requirements of paragraph (2), continue to calculate the accumulated RIN for the mast by multiplying all takeoff and external load lifts by the RIN factors defined in columns (D) and (G) of Table 1 of Appendix 1. \n\n\t\t(7) After accomplishing the requirements of paragraph (2), continue to count the hours TIS for the mast. Any hours TIS for the mast while installed on a helicopter operated with a hub spring or if the history of a hub spring installation is unknown must be factored in accordance with the instructions in Appendix 1. \n\n\t\t(8) This AD establishes a retirement life of 265,000 accumulated RIN or 15,000 hours TIS, whichever occurs first, for mast, P/N 204-011-450-007, -105, and -109. \n\n\t\t(9) Within 10 days after completing the inspections required by paragraph (5) of this AD, send the information contained on the AD compliance inspection report sample format contained in Appendix 2 to the Manager, Rotorcraft Certification Office, Federal Aviation Administration, Fort Worth, Texas, 76193-0170, USA. Reporting requirements have been approved by the Office of Management and Budget and assigned OMB control number 2120-0056. \n\n\n\n\nFigure 1 \n\n\n\n\n\n\nFigure 2 Snap Ring Groove/Spline Intersection \n\n\n\n\n\n\n\n\n\n\nCutaway View Looking Down from Inside Snap Ring Groove \n\nTypical Burrs at Snap Ring Groove/Spline Intersection \nBurrs are to be Inspected at 200x Minimum Magnification \n\nFigure 3 Typical Burr at Snap Ring Groove \n\n\n\t(b) For the trunnion, P/N 204-011-105-001: \n\n\t\t(1) Within 10 days, create a component history card or equivalent record for the trunnion and record the hours TIS accumulated on the trunnion. If the TIS cannot be determined, enter 900 hours for each year from the date the trunnion was installed. \n\n\t\t(2) Remove any trunnionwith 14,900 or more hours TIS from service within the next 100 hours TIS. \n\n\t\t(3) Remove any trunnion with less than 14,900 hours TIS from service at or before 15,000 hours TIS. \n\n\n\tNOTE 5: Paragraph (b) of this AD continues the requirements of the superseded AD for the trunnion. \n\n\t(c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Rotorcraft Certification Office, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Certification Office. \n\n\tNOTE 6: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Manager, Rotorcraft Certification Office. \n\n\t(d) Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the helicopter to a location where therequirements of this AD can be accomplished. \n\n\t(e) This amendment becomes effective on December 26, 2000, to all persons except those persons to whom it was made immediately effective by Emergency AD 2000-22-51, issued November 2, 2000, which contained the requirements of this amendment. \n\nAPPENDIX 1\nAppendix 1 to AD 2000-22-51\nInstructions for Calculating RIN and Revised Hours TIS\n\n\nDefinitions for the Retirement Index Number:\n\nThe overall fatigue life of a main rotor mast is a function of the number of cycles of torque, lift, and bending loads applied to it during the various modes of operation. The mast experiences both high cycle fatigue and low cycle fatigue during operation.\n\nThe high cycle fatigue life of the mast is a function of high frequency but relatively low level cyclic loads, which are primarily induced by rotor rpm. The high cycle fatigue life limit for the mast is defined in terms of hours TIS because rotor rpm is basically a constant value.\n\nThe lowcycle fatigue life of the mast is a function of the number of less frequent but relatively high level cyclic loads experienced primarily during takeoffs and external load lifts. The low cycle fatigue life limit for the mast is expressed in terms of the accumulated Retirement Index Number (RIN).\n\nA load cycle is a power cycle caused by a repeating or fluctuating load that alternates from a starting power value, goes to a higher power value, and returns to the starting power value.\n\nThe accumulated RIN is defined as the total number of load cycles multiplied by a RIN factor to account for the difference in torque levels applied to the same mast (since manufactured) when installed in different helicopter models. The level of torque applied to the mast is directly proportional to the transmission output horsepower.\n\nThe unfactored hours TIS is the time from the moment a helicopter leaves the surface of the earth until it touches it at the next point of landing with no factors applied.\n\nThe FACTORED flight hours is the unfactored hours TIS multiplied by a frequency of event hour factor based on the torque (horsepower) of the helicopter model in which it was installed and the usage of the helicopter.\n \nThe revised hours TIS is the new hours TIS for the mast as determined by following the instructions in this appendix.\n\nAn external load lift is defined as a lift where the load is carried, or extends, outside of the aircraft fuselage.\n\nCalculation of Retirement Index Number and Revised Hours TIS:\n\nThere are two methods for calculating the accumulated RIN and the revised hours TIS, depending on the available service history information for the mast. In some cases, one method will be used for a portion of the mast service history, and the other method will be used for another portion of the mast service history. Both methods require knowledge of all the helicopter models in which the mast was installed.\n\nCalculation of RIN and Revised Hours TIS when theExact Number of Takeoffs and External Load Lifts is Known(Reference Tables 1 and 3):\n\nTable 1 of Appendix 1 is the worksheet for calculating the accumulated mast RIN when the exact number of takeoffs and external load lifts is known. Table 3 of Appendix 1 is the worksheet that has the frequency of event hour factors to calculate the FACTORED flight hours for the unfactored hours TIS for the mast while installed on a helicopter operated with a hub spring or if the hub spring installation history is unknown.\n\nThe RIN factor for each external load lift is twice that specified for each takeoff because two torque events are experienced during a typical external load lift.\n\nUsing Table 1, calculate accumulated RIN as follows:\n\n1.\tEnter the total number of takeoffs for the particular mast model/helicopter model combination in column (C).\n\n2.\tMultiply the value entered in column (C) by the RIN factor listed in column (D), and enter the result in column (E). This is the total accumulated RIN due to takeoffs.\n\n3.\tEnter the total number of external load lifts for the particular mast model/helicopter model combination in column (F).\n\n4.\tMultiply the value entered in column (F) by the RIN factor listed in column (G), and enter the result in column (H). This is the accumulated RIN due to external load lifts.\n\n5.\tAdd the values from column (E) and column (H) and enter the result in column (I). This is the total accumulated RIN to-date for the mast for the particular mast model/helicopter model combination.\n\n6.\tAdd the accumulated RIN subtotals for the various mast model/helicopter combinations in column (I) and enter the result in the space provided. This is the total accumulated RIN for the mast.\n\nUsing Table 3, calculate the revised hours TIS as follows:\n\n7.\tDetermine the unfactored hours TIS for the mast while installed on a helicopter operated with a hub spring or if the hub spring installation history is unknown for each of the particular mast model/helicopter model combinations.\n\n8.\tDetermine the frequency of events per hour for each of the particular mast model/helicopter model combinations dividing the combined number of takeoffs and external load lifts by the corresponding unfactored hours TIS.\n\n9.\tMultiply the value for unfactored hours TIS for each of the particular mast model/helicopter model combinations by the appropriate value in column (E) of Table 3 for the frequency of event hour factor. These are the total FACTORED flight hours for the particular mast model/helicopter model combinations.\n\n10.\tAdd the FACTORED flight hour subtotals for each of the particular mast model/helicopter model combinations. This is the total FACTORED flight hours for the mast while installed on a helicopter operated with a hub spring or if the hub spring installation history is unknown.\n\n11.\tDetermine the unfactored hours TIS for the mast while installed on a helicopter operated without a hub spring.\n\n12.\tAdd to the total FACTORED flight hours for the mast while installed on a helicopter operated with a hub spring or if the hub spring installation history is unknown to the unfactored hours TIS as determined in step 11. This is the total revised hours TIS for the mast when the exact number of takeoffs and external load lifts is known.\n\nCalculation of RIN and Revised Hours TIS when Exact Number of Takeoffs and External Load Lifts is Unknown (Reference Tables 2, 3, and 4):\n\nTables 2, 3, and 4 of Appendix 1 are the worksheets for calculating the FACTORED flight hours and accumulated mast RIN when the exact number of takeoffs and external load lifts is unknown. \n\nUsing Tables 2, 3, and 4, calculate the accumulated mast RIN and revised hours TIS as follows:\n\n1.\tEnter the unfactored hours TIS for the particular mast model/helicopter model combination in column (C) of Tables 2 and 3.\n\n2.\tUsing service history for the mast, select the appropriate frequency of event hour factor from column (E) of Tables 2 and 3 based on the total combined number of takeoffs and external load lifts per hour shown in column (D).\n\n3.\tMultiply the value for unfactored hours TIS entered in column (C) by the appropriate value in column (E) for the frequency of event hour factor as determined in step 2. Enter the result in column (F) of Tables 2 and 3. This is the total FACTORED flight hours for the particular mast model/helicopter model combination.\n\n4.\tEnter the value for FACTORED flight hours from column (F) of Tables 2 and 3 into column (C) of Table 4.\n\n5.\tUsing Table 4, multiply the value for FACTORED flight hours in column (C) by the appropriate RIN conversion factor listed in column (D), by the appropriate RIN adjustment factor in column (E), and enter the result in column (F). This is the accumulated RIN to-date for the particular mast model/helicopter model combination.\n\n6.\tAdd the accumulated RIN subtotals for the various mast model/helicopter model combinations in column (F) of Table 4 andenter the result in the space provided. This is the total accumulated RIN for the mast.\n\n7.\tAdd the factored flight hour subtotals for the various mast model/helicopter model combinations as determined in steps 1 through 4. This is the total revised hours TIS for the mast when the exact number of takeoffs and external load lifts is unknown.\n\n\nSample Mast Calculation\n\nGiven the following known service history for the mast:\n\nMast, P/N 204-011-450-007, was first purchased as a United States military surplus part with valid historical records. The mast had accumulated 550 hours military TIS on an Army UH-1H with a hub spring installed.\n\nThe mast was first installed on a restricted category UH-1H former military helicopter for 250 hours TIS. The helicopter had a rating of 1100 takeoff horsepower (T.O. hp) at sea level standard day conditions (SLS), and the operation of the helicopter without a hub spring cannot be determined. The helicopter was used for fire fighting operations and the exact number of takeoffs and external load lifts is unknown. It is known, however, that the helicopter averaged less than 15 combined takeoffs and external load lifts per hour.\n\nThe mast was then removed and subsequently installed on a restricted category UH-1E former military helicopter (1100 T.O. hp SLS rating) without a hub spring for 450 hours TIS. It is known that the helicopter was used primarily for aerial surveying for the first 200 hours of operation. The exact number of takeoffs and external load lifts is unknown, but it is known that the helicopter averaged less than 16 takeoffs per hour, with no external load lifts. It was subsequently used for repeated heavy lift operation for the next 250 hours of operation and averaged between 25 and 31 combined takeoffs and external load lifts per hour during this period of time.\n\nThe mast was then removed and installed on another restricted category UH-1H former military helicopter (1100 T.O. hp SLS rating) for a total of 150 hours TIS with accurate records indicating that it experienced 100 takeoffs and 2,450 external load lifts. A hub spring was installed on the helicopter for the first 50 hours of operation with a calculated average of 19 combined takeoffs and external load lifts per hour (as determined from aircraft records for the first 50 hours of operation). The hub spring was subsequently removed for the remaining 100 hours TIS.\n\nCalculate the FACTORED flight hours and total accumulated RIN for the mast as follows:\n\nFACTORED Flight Hours and Accumulated RIN while installed in U.S. military Model UH-1H:\n\nCalculate FACTORED flight hours from Table 3 as follows: \n\nFACTORED Flight Hours \t=\t(unfactored hours TIS) x (frequency of event hour factor)\n\t=\t(column C) x (column E)\n\t=\t(550) x (10)\n\t=\t5,500 hours\n\nThen using Table 4, calculate the accumulated RIN as follows:\n\nAccumulated RIN \t= (FACTORED flight hours) x (RIN conversion factor) x (RIN adjustment factor)\n\t= (column C)x (column D) x (column E) \n\t= (5,500) x (20) x (1)\n\n\t= 110,000 RIN\n\nFACTORED Flight Hours and Accumulated RIN while installed in restricted category Model UH-1H:\n\nCalculate FACTORED flight hours from Table 3 as follows:\n\nFACTORED Flight Hours \t=\t(unfactored hours TIS) x (frequency of event hour factor)\n\t=\t(column C) x (column E)\n\t=\t(250) x (14)\n\t=\t3,500 hours\n\nThen using Table 4, calculate the accumulated RIN as follows:\n\nAccumulated RIN \t= (FACTORED flight hours) x (RIN conversion factor) x (RIN adjustment factor)\n\t= (column C) x (column D) x (column E)\n\t= (3,500) x (20) x (1)\n\n\t= 70,000 RIN\n\nFACTORED Flight Hours and Accumulated RIN while installed in restricted category Model UH-1E:\n\nCalculate FACTORED flight hours from Table 2 as follows:\n\nFACTORED Flight Hours \t=\t(unfactored hours TIS) x (frequency of event hour factor)\n(for first 200 hrs.)\t=\t(column C) x (column E)\n\t=\t(200) x (5)\n\t=\t1,000 hours\n\nFACTORED Flight Hours \t=\t(unfactored hours TIS)x (frequency of event hour factor)\n(for next 250 hrs.)\t\t=\t(column C) x (column E)\n\t\t=\t(250) x (10)\n\t\t=\t2,500 hours\n\nThen using Table 4, calculate the accumulated RIN as follows:\n\nAccumulated RIN \t= (FACTORED flight hours) x (RIN conversion factor) x (RIN adjustment factor)\n\t= (column C) x (column D) x (column E)\n\t= (1,000) x (20) x (1)\t+ (2,500) x (20) x (1)\n\t= 20,000 + 50,000 \n\n\t= 70,000 RIN\n\nFACTORED Flight Hours and Accumulated RIN while installed in another restricted category Model UH-1H:\n\nCalculate the accumulated RIN from Table 1 and the given number of takeoffs and external load lifts as follows:\n\nAccumulated RIN = (number of takeoffs x RIN factor per takeoff) + (number of external load \nlifts x RIN factor per external load lifts.\n\n= (column C) x (column D) + (column F) x (column G)\n= (100) x (3) + (2,450) x (6)\n= 15,000 RIN\n\nCalculate the FACTORED flight hours for the mast while installed on a helicopter operated with a hub spring or if the hub spring installation history is unknown using the frequency of event hour factors from Table 3 as follows:\n\t\t\nFACTORED Flight Hours \t=\t(unfactored hours TIS) x (frequency of event hour factor)\n(w/ hub spring)\t=\t(column C) x (column E)\n\t=\t(50) x (16)\n\t=\t800 hours\n\nUnfactored Hours TIS \t=\t(unfactored hours TIS) \n(w/o hub spring)\t\t=\t100 hours\n\nNote that the FACTORED flight hours are not used in the accumulated RIN calculations when the number of takeoffs and external load lifts is known.\n\n\nCalculate the Total Accumulated RIN and Revised Hours TIS as follows: \n\nThe total accumulated RIN to-date for the mast is the sum of the subtotals from Tables 1 and 4.\n\nTotal Accumulated RIN \t= 110,000 + 70,000 + 70,000 + 15,000\n\t= 265,000\n\nThe total FACTORED flight hours for the mast is the sum of the subtotals from Tables 2 and 3 and the total FACTORED flight hours as determined in the preceding step 12 when the exact number of takeoff and external load lifts is known.Total FACTORED Flight Hours\t= 5,500 + 3,500 + 1,000 + 2,500 + 800\n\t\t= 13,300 hours\n\nThe revised hours TIS to-date for the mast is the sum of the total FACTORED flight hours and the additional unfactored hours TIS for the mast while installed on a helicopter operated without a hub spring and the exact number of takeoffs and external load lifts is known.\n\nRevised Hours TIS\t= 5,500 + 3,500 + 1,000 + 2,500 + 800 + 100\n= 13,300 + 100\n\t\t= 13,400 hours\n\nBoth the total accumulated RIN and the revised hours TIS need to be determined and checked for exceeding the allowable life limits for the mast. Also, note that the recalculated total accumulated RIN for this sample mast would be 265,000 RIN. Therefore, this mast would be removed from service.\n\nThe values for the sample problem are shown in Tables 1 - 4 for illustration purposes only. The FACTORED flight hours TIS shown in the brackets in Table 3 are calculated for the mast while installed on a helicopter operated with a hub spring or if the hub spring installation history is unknown and the exact number of takeoffs and external load lifts is known. These FACTORED flight hours are not used in the accumulated RIN calculations.\n\nMast RIN Calculation Based on Takeoffs and External Load Lifts\n\n\nMast A/C Model Installation\nMast P/N\n204-011-450\nNumber Of Takeoffs\nRIN Factor Per Takeoff\nTotal Takeoff RIN\nNumber of External Load Lifts\nRIN Factor Per External Load Lift\nTotal External Load Lift RIN\nAccumulated RIN\n(A)\n(B)\n(C)\n(D)\n(E)=(C) x (D)\n(F)\n(G)\n(H)=(F) x (G)\n(I)=(E) + (H)\nRestricted Category TIS \n204-011-450-007\n\n0.25\n\n\n0.5\n\n\n(<700 T.O. hp SLS)\n204-011-450-105\n\n0.25\n\n\n0.5\n\n\n\n204-011-450-109\n\n0.25\n\n\n0.5\n\n\nRestricted Category TIS \n204-011-450-007\n\n1.5\n\n\n3\n\n\n(7001290 T.O. hp SLS)\n204-011-450-105\n\nFAA*\n\n\n\n\n\n\n204-011-450-109\n\n\n\n\n\n\n\nTotal RIN=\n\n\n\n\n\n\n\n15,000\n*Contact FAA at (817) 222-5447\nAppendix 1 - Table 1\n\n\n\nCalculation of Mast FACTORED Flight Hours (Without a Hub Spring Installed)\n\n\nMast\nA/C Model\nInstallation\nMast\nP/N 204-011-450\n(without a hub spring installed)\nUnfactored\nHours TIS\non Model\nFrequency Of Events Per Hour\nFrequency of Event Hour Factor\nFACTORED Flight Hours On Model\n(A)\n(B)\n(C)\n(D)\n(E)\n(F)= (C) x (E)\nRestricted Category TIS \n(<700 T.O. hp SLS)\n204-011-450-007, -105, \nor -109\n\n1.0-37.00\n1.00\n\n\n\n\n37.01-46.00\n1.25\n\n\n\n\n46.01-55.00\n1.50\n\n\n\n\n55.01-63.00\n1.75\n\n\n\n\nGreater than 63.00\nContact FAA*\n\n\n\n\nUnknown\n1.75\n\nRestricted Category TIS \n(7001290 T.O. hp SLS)\n\n\nAll\nContact FAA*\n\n*Contact FAA at (817) 222-5447\nAppendix 1 - Table 2\n\n\n\n\nCalculation of Mast FACTORED Flight Hours (With a Hub Spring Installed)\n\n\nMast\nA/C Model\nInstallation\nMast\nP/N 204-011-450\n(with a hub spring or the history of a hub spring installed is unknown)\nUnfactored\nHours TIS\non Model\nFrequency \nOf Events\nPer Hour\nFrequency\nof Event\nHour Factor\nFACTORED\nFlight Hours \nOn Model\n(A)\n(B)\n(C)\n(D)\n(E)\n(F) = (C) x (E)\nRestricted Category TIS (<700 T.O. hp SLS)\n204-011-450-007, -105,\n\n1.0-6.00\n10.00\n\n\nor -109\n\n6.01-12.00\n10.2512.01-21.00\n10.50\n\n\n\n\n21.01-39.00\n11.00\n\n\n\n\n39.01-63.00\n11.75\n\n\n\n\nGreater than 63.00\nContact FAA*\n\n\n\n\nUnknown\n11.75\n\nRestricted Category TIS (700\n15.01-21.00\n16.00\n<800>\n\n\n\n21.01-33.00\n20.00\n\n\n\n\n33.01-45.00\n24.00\n\n\n\n\n45.01-61.00\n30.00\n\n\n\n\nGreater than 61.00\nContact FAA*\n\n\n\n\nUnknown\n30.00\n\nRestricted Category TIS \n(11001290 hp T.O. SLS)\nor -109\n\nAll\nContact FAA*\n\n\n\n\n\n\n\n*Contact FAA at (817) 222-5447\nAppendix 1 - Table 3\n\n\n\n\nMast RIN Calculation Based on Hours Time-in-Service\n\n\nMast A/C Model\nInstallation\nMast\nP/N 204-011-450\nFACTORED\nFlight Hours \nOn Model\nRIN \nConversion\nFactor\nRIN\nAdjustment\nPer AD 2000-15-52\nAccumulated\nRIN\n(A)\n(B)\n(C)\n(From Table 2\nof Appendix I)\n(D)\n(E)\n(F)\n=(C) x (D) x (E)\nRestricted Category\n204-011-450-007\n12,500\n20\n1\n250,000\nor Military TIS with\n204-011-450-105\n\n20\n1\n\n(<1290 T.O. hp SLS)\n204-011-450-109\n\n20\n1\n\nRestricted Category\n204-011-450-007\n\n\n\n\nor Military TIS with\n204-011-450-105\nContact FAA*\nContact FAA*\nContact FAA*\nContact FAA*\n(>1290T.O. hp SLS)\n204-011-450-109\n\n\n\n\nTotal RIN=\n\n\n\n\n250,000\n*Contact FAA at (817) 222-5447\nAppendix 1 - Table 4\n\nSubtotals for the FACTORED Flight Hours and Accumulated RIN\nFor Table 4 of the Sample Mast Calculation:\n\n\t\t\t\t\t\t\tFACTORED\t\t\tAccumulated\n\t\t\t\t\t\t\tFlight Hours\t\t\t\tRIN\t\n\n\t\t\t\t\t\t\t 5,500\tX\t20\t=\t110,000\n\t\t\t\t\t\t\t 3,500\tX\t20\t=\t 70,000\n\t\t\t\t\t\t\t 3,500\tX\t20\t=\t 70,000\n\t\t\t\t\t\t\t__________________________________\n\t\t\t\t\t\t\t12,500\t\t\t\t250,000\n\n\n\nAPPENDIX 2\n\nAPPENDIX 2 to AD 2000-22-51\n\nAD COMPLIANCE INSPECTION REPORT (Sample Format)\nP/N 204-011-450-007/-105/-109 MAIN ROTOR MAST\n\nProvide the following information and mail or fax it to:\n\nManager, Rotorcraft Certification Office\nFederal Aviation Administration\nFort Worth, Texas, 76193-0170, USA\nFax: 817-222-5783\n\nAircraft Registration No:\n\nHelicopter Model:\n\nHelicopter S/N:\n\nMast P/N:\n\nMast S/N:\n\nMast RIN:\n\nMast Total TIS:\n\n\nInspection Results\n\nWere any radii during inspection of this mast determined to be less than 0.020 inch? If yes, what was the dimension measured? \nWas a burr found in the inspected snap ring grooves? \nWere cracks noted during the inspection? \nWho performed this inspection?\nProvide any other comments?