87-20-03 R2: Seat Tracks

87-20-03 R2 CESSNA: Amendment 39-5729, as revised by Amendment 39-5863, is further revised by Amendment 39-6669. Docket No. 86-CE-71-AD. \n\n\tApplicability: To the following model airplanes, certificated in any category. \n\n\nModels\nSerial Numbers\n150A, 150B, 150C, 150D, 150E, 150F, \n150G, 150H, 150J, 150K, 150L, 150M\n\n15059019 thru 15079405\nA150K, A150L, A150M\nA1500001 thru A1500734\n152, A152 \nAll\n170, 170A, 170B \n18000 through 27169\n172, 172A, 172B, 172C, 172D, 172E, \n172F, 172G, 172H, 172I, 172K, 172L, \n172M, 172N, 172P, 172Q \n\n\nAll\nP172D \nP17257120 thru P17257188\nR172E, R172F, R172G, R172H, R172J \nAll\nR172K \nR1722000 thru R1723454\n172RG\n172RG0001 thru 172RG1191\n175, 175A\n55001 thru 56777\n175B, 175C\n17556778 thru 17557119\n177, 177A, 177B, 177RG\nAll\n180, 180A \n30000 thru 32999\n180A, 180B, 180C \n50000 thru 50911\n180D, 180E, 180F, 180G, 180H, 180J, 180K\n18050912 thru 18053203\n182, 182A, 182B, 182C, 182D, 182E, \n182F, 182G, 182H, 182J, 182K,182L, \n182M, 182N, 182P, 182Q, 182R, T182, \nR182,TR182\n\n\n\nAll\n185, 185A, 185B, 185C, 185D, 185E, \nA185E, A185F \n\nAll\n188, 188A, A188, A188A, 188B, A188B,\nT188C\n\nAll\n190, 195, 195A, 195B\n7001 thru 7999, and 16000 thru 16183\n206, U206, U206A, U206B, U206C, U206D, U206E, U206F, U206G, TU206A, TU206B, TU206C, TU206D, TU206E, \nTU206F, TU206G\n\n\nAll\nP206, P206A, P206B, P206C, P206D, \nTP206A, TP206B, TP206C, TP206D\n\nP206-0001 thru P206-0603, &\nP206E, TP206E\nP20600604 thru P20600647\n207, T207, 207A, T207A\nAll\n210, 210A, 210B, 210C, 210D, 210E, \n210F, 210G, 210H, 210J, 210K, 210L,\n210M, 210N, P210N, T210F, T210G,\nT210H, T210J, T210K, T210L, T210M,\nT210N, 210R, T210R, P210R \n\n\n\n\nAll\n210-5 (205), 210-5A (205A)\n205-0001 thru 205-0577\n336 \n336-0001 thru 336-0195\n337, 337A, 337B, 337C, 337D, 337E, \n337F, 337G, 337H, T337B, T337C, T337D, \nT337E, T337F, T337G, T337H, P337H, T337H-SP \n\n\nAll\nT303\nAll\nF150G, F150H, F150J, F150K, F150L, \nF150M, FA150K,FA150L, FRA150L, \nFRA150M \n\n\nAll\nFA152, F152 \nAll\nFP172 \nFP172-0001 thru FP172-0003 \nF172F, F172G, F172H, F172K, \nF172L, F172M, F172N, F172P, \nFR172E, FR172F, FR172G, FR172H, \nFR172J, FR172K \n\n\n\nAll\nF177RG \nAll \nF182P, F182Q\nAll \nFR182\nAll \nF337E, F337F, F337G, F337H \nAll \nFP337 \nAll \n \t \nCompliance: Required as follows, unless already accomplished per AD 87-20-03 R1, Amendment 39-5863. \n\nI.\tFor airplanes operating for hire: \n\n\t(A)\tFor airplanes having less than 1,000 hours time-in-service (TIS) on the effective date of this AD, accomplish the AD requirements prior to the accumulation of 1,100 hours TIS; \n\n\t(B)\tFor airplanes having 1,000 or more hours TIS on the effective date of this AD, accomplish the AD requirements within the next 100 hours TIS; \n\n\t(C)\tFollowing the actions of (A) or (B) above, repeat the inspection requirements of this AD at each 100 hours TIS. These inspections can be accomplished at the next scheduled inspection or the next100 hours, whichever is later.\n\nII.\tFor airplanes operating under FAR Part 91 (not for hire): \n\n\t(A)\tFor airplanes having less than 1,000 hours TIS on the effective date of this AD, accomplish the AD requirements at the next annual inspection after the accumulation of 1,000 hours TIS; \n\n\t(B)\tFor airplanes having 1,000 or more hours TIS on the effective date of this AD, accomplish the AD requirements at the next annual inspection; \n\n\t(C)\tFollowing the actions of (A) or (B) above, repeat the AD requirements at each annual inspection thereafter. To assure proper engagement of the seat locking mechanism and to preclude inadvertent seat slippage, accomplish the following on each pilot and copilot seat and all associated seat rails: \n\n\tNOTE 1:\tParagraph (a) of this AD is essentially unchanged from AD 87-20-03 R1, Amendment 39-5863 and is reprinted here for the convenience of the reader. \n\n\t(a)\tIn accordance with the appropriate compliance time requirement above, accomplish the following: \n\n\t\t(1)\tMeasure each hole in the seat track(s) for excessive wear. When checking these holes for wear, an allowance of 0.020 inches below the edge of the normal surface is permitted for the required measurement. \n\n\t\t\t(i)\tIf the wear dimension across any hole exceeds 0.36 inches but does not exceed 0.42 inches (see Figure 1), continue to measure each hole every 100 hours TIS for excessive wear. \n\n\t\t\t(ii)\tIf the wear dimension across any hole exceeds 0.42 inches, prior to further flight, replace the seat track. \n\n\t(2)\tVisually inspect the seat rail holes for dirt and any debris, which may preclude engagement of the seat pin(s). Prior to further flight, remove any such material. \n\n\t(3)\tLift up on the forward edge of each seat to eliminate all vertical play. In this position, measure the depth of engagement of each seat pin. If the engagement of any pin is less than 0.15 inches (see Figure 2), prior to further flight, replace or repair necessary components to achievea seat pin engagement of 0.15 inches or greater. If the track is worn, this dimension is measured from the worn surface, not the manufactured surface. \n\n\t(4)\tVisually inspect seat rollers for flat spots. Assure all rollers and washers, which are meant to rotate, turn freely on their axle bolts (or bushings if installed). Prior to further flight, replace rollers having flat spots and any worn washers. If there is any binding between the bores of the rollers, washers, and axle bolts (or bushings if installed), prior to further flight, remove, clean, and reinstall these parts. \n\n\tNOTE 2:\tDo not lubricate rollers, washers, axle bolts or bushings as the lubricant will attract dust and other particles which can cause binding. \n\n\t(5)\tMeasure the wall thicknesses of the roller housing and the tang (see Figure 2). If the tang thickness has worn to less than 1/2 the housing thickness, prior to further flight, replace the roller housing. \n\n\t(6)\tCheck the spring(s) that keep the lock pin(s) in position in the track holes for positive engagement action. Prior to further flight, replace any spring which does not provide positive engagement. \n\n\t(7)\tVisually inspect the seat tracks for cracks in accordance with Cessna Single Engine Service Information Letter SE83-6, dated March 11, 1983. Prior to further flight, replace any seat rail exceeding the crack criteria as specified in SE83-6 with an airworthy rail. \n\n\t(b)\tThe options listed in AD 87-20-03 R1, Amendment 39-5863, for the temporary operation of the airplane are no longer an acceptable means of compliance with the requirements of this AD, but may be retained if desired. \n\n\t(c)\tAirplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. \n\n\t(d)\tAny parts replaced per this AD are exempt from the inspections required herein until such parts have attained 1,000 hours TIS. \n\n\t(e)\tAn alternate method of compliance or adjustment of the initial or repetitive compliancetimes, which provides an equivalent level of safety, may be approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Wichita, Kansas 67209. \n\n\tNOTE 3:\tThe request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. \n\n\tAll persons affected by this directive may obtain copies of the document referred to herein upon request to the Cessna Aircraft Company, Customer Service, P.O. Box 1521, Wichita, Kansas 67201; or may examine this document at the Federal Aviation Administration, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. \n\n\tAirworthiness Directive 87-20-03 R2 revises AD 87-20-03 R1 (Amendment 39-5863) which revised AD 87-20-03 (Amendment 39-5729). \n\n\tThis amendment (39-6669, AD 87-20-03 R2) becomes effective on September 24, 1990.