SEB95-3 R1 - McFarlane Aviation

172Q 1983 17276032, 17276042, 17276045 172Q 1983 17276051, 17276052, 17276054 172Q 1984 17276101, 17276109, 17276140 SEB95-3 Revision 1 September 17, 2001 Page 3 172Q 1984 17276147, 17276188, 17276211 R172E (T41) 1967 thru 1968 R172-0001 thru R172-0335 R172F (T41) 1969 R172-0336 thru R172-0409 R172G (T41) 1969 thru 1970 R1720410 thru R1720444 R172H (T41) 1971 R1720445 thru R1720494 R172H (T41) 1972 R1720495 thru R1720546 R172H (T41) 1973 thru 1976 R1720547 thru R1720620 R172J 1974 P17257189 R172K 1977 R1722000 thru R1722724 R172K 1978 R1722725 thru R1722929 R172K 1979 R1722930 thru R1723199 R172K 680 R172K 1980 R1723200 thru R1723397 R172K 1980 R1723397 thru R1723399 R172K 1981 R1723400 thru R1723454 172RG 1980 172RG0001 thru 172RG0570 172RG 1981 172RG0571 thru 172RG0890 172RG 691 172RG 1982 172RG0891 thru 172RG1099 172RG 1983 172RG1100 thru 172RG1144 172RG 1984 172RG1145 thru 172RG1177 172RG 1985 172RG1178 thru 172RG1191 175 1958 thru 1959 55001 thru 56238 175 28700A 175A 1960 56239 thru 56777 175A 619 175B 1961 17556778 thru 17557002 175C 1962 17557003 thru 17557119 P172D 1963 P17257120 thru P17257188 180 1953 thru 1956 30000 thru 32661 180 604, 614 180A 1957 32662 thru 32999 180A 1957 thru 1958 50001 thru 50355 180B 1959 50356 thru 50661 180C 1960 50662 thru 50911 180C 624 180D 1961 18050912 thru 18051063 180E 1962 18051064 thru 18051183 180F 1963 18051184 thru 18051312 180G 1964 18051313 thru 18051445 180H 1965 thru 1972 18051446 thru 18052284 SEB95-3 Revision 1 Page 4 September 17, 2001 180H 645 180J 1973 thru 1976 18052285 thru 18052489 180J 1973 thru 1976 18052491 thru 18052770 180K 1977 18052771 thru 18052905 180K 1978 18052906 thru 18053000 180K 1979 18053001 thru 18053115 180K 18052490 180K 1980 18053116 thru 18053167 180K 1981 18053168 thru 18053203 182 1956 33000 thru 33842 182 613 182A 1957 33843 thru 34753 182A 1958 34755 thru 34999 182A 1958 51001 thru 51556 182B 1959 51557 thru 51622 182B 1959 51624 thru 52358 182B 34754 182C 1960 52359 thru 53007 182C 631 182D 1961 18253008 thru 18253598 182D 1961 51623 182E 1962 18253599 thru 18254423 182F 1963 18254424 thru 18255058 182G 1964 18255059 thru 18255844 182H 1965 18255846 thru 18256684 182H 634 182J 1966 18256685 thru 18257625 182K 1967 18257626 thru 18257698 182K 1967 18257700 thru 18258505 182K 1967 18255845 182L 1968 18258506 thru 18259305 182M 1969 18259306 thru 18260055 182M 18257699 182N 1970 18260056 thru 18260445 182N 1971 18260446 thru 18260825 182P 1972 18260826 thru 18261425 182P 1973 18261426 thru 18262465 182P 1974 18262466 thru 18263475 182P 1975 18263476 thru 18263478 182P 1975 18263480 thru 18264295 182P 675 SEB95-3 Revision 1 September 17, 2001 Page 5 182P 1976 18264296 thru 18265175 182Q 1977 18265176 thru 18265965 182Q 1978 18265966 thru 18266590 182Q 18263479 182Q 1979 18266591 thru 18267300 182Q 1980 18267301 182Q 1980 18267303 thru 18267715 182R/T182 1981 18267716 thru 18268055 182R/T182 18267302 182R/T182 1982 18268056 thru 18268293 182R/T182 1983 18268294 thru 18268368 182R/T182 1984 18268369 thru 18268434 182R/T182 1985 18268435 thru 18268541 182R 1986 18268542 thru 18268586 R182 1978 R18200002 thru R18200583 R182/TR182 1979 R18200584 thru R18201313 R182/TR182 R18200001 R182/TR182 1980 R18201314 R182/TR182 1980 R18201316 thru R18201628 R182/TR182 1981 R18201629 thru R18201798 R182/TR182 1982 R18201799 thru R18201928 R182/TR182 1983 R18201929 thru R18201973 R182/TR182 1984 R18201974 thru R18201999 R182/TR182 1985 R18202000 thru R18202031 R182/TR182 R18201315 R182/TR182 1986 R18202032 thru R18202039 185 1961 185-0001 thru 185-0237 185 632 185A 1962 185-0238 thru 185-0512 185B 1963 185-0513 thru 185-0653 185C 1964 185-0654 thru 185-0776 185D 1965 185-0777 thru 185-0967 185E 1966 185-0968 thru 185-1149 A185E 1966 185-0968 thru 185-1149 A185E 1967 185-1150 thru 185-1300 A185E 1968 185-1301 thru 185-1447 A185E 1969 185-1448 thru 185-1599 A185E 1970/1971 18501600 thru 18501934 A185E 1972 18501935 thru 18502090 A185F 1973 18502091 thru 18502299 A185F 1973 18502301 thru 18502310 SEB95-3 Revision 1 Page 6 September 17, 2001 A185F 652 A185F 1974 18502311 thru 18502565 A185F 1975 18502566 thru 18502838 A185F 1976 18502839 thru 18503153 A185F 1977 18503154 thru 18503458 A185F 1978 18503459 thru 18503683 A185F 1979 18503684 thru 18503938 A185F 18502300 A185F 1980 18503939 thru 18504138 A185F 1981 18504139 thru 18504328 A185F 1982 18504329 thru 18504394 A185F 1983 18504395 thru 18504415 A185F 1984 18504416 thru 18504424 A185F 1985 18504425 thru 18504448 188 1966 thru 1969 188-0001 thru 188-0572 188 653 A188 1966 thru 1969 188-0001 thru 188-0572 A188 653 188A 1970 thru 1971 18800573 thru 18800832 A188A 1970 thru 1971 18800573 thru 18800832 188B 1972 thru 1975 18800833 thru 18802348 A188B 1972 thru 1983 18800833 thru 18803973 A188B 1972 thru 1983 18800967T thru 18803973T A188B 678T T188C 1979 thru 1983 T18803325T thru T18803974T T188C 1979 thru 1983 T18803307T, T18803308T T188C T18802839T 210-5 (205) 1963 205-0001 thru 205-0480 210-5(205) 641 210-5 (205A) 1964 205-0481 thru 205-0577 206 1964 206-0001 thru 206-0275 P206 1965 P206-0002 thru P206-0160 P206A 1966 P206-0161 thru P206-0306 TP206A 1966 P206-0161 thru P206-0306 P206B/ TP206B 1967 P206-0307 thru P206-0419 P206C/ TP206C 1968 P206-0420 thru P206-0519 P206D/ TP206D 1969 P206-0520 thru P206-0603 P206E/ TP206E 1970 P20600604 thru P20600647 SEB95-3 Revision 1 September 17, 2001 Page 7 P206E/ TP206E P206-0001 U206 1965 U206-0276 thru U206-0437 U206A 1966 U206-0438 thru U206-0656 TU206A 1966 U206-0487 thru U206-0656 U206B/ TU206B 1967 U206-0657 thru U206-0914 U206C/ TU206C 1968 U206-0915 thru U206-1234 U206D/ TU206D 1969 U206-1235 thru U206-1444 U206D/ TU206D 1970 U20601445 thru U20601587 U206E/ TU206E 1971 U20601588 thru U20601700 U206F/ TU206F 1972 U20601701 thru U20601874 U206F/ TU206F 1973 U20601875 thru U20602199 U206F/ TU206F 1974 U20602200 thru U20602579 U206F/ TU206F 1975 U20602580 thru U20602588 U206F/ TU206F 1975 U20602590 thru U20603020 U206F/ TU206F 1976 U20603021 thru U20603521 U206G/ TU206G 1977 U20603522 thru U20604074 U206G/ TU206G 676 U206G/ TU206G 1978 U20604075 thru U20604649 U206G/ TU206G 1979 U20604650 thru U20605309 U206G/ TU206G U20602589 U206G/ TU206G 1980 U20605310 thru U20605919 U206G/ TU206G 1981 U20605920 thru U20606439 U206G/ TU206G 1982 U20606440 thru U20606699 U206G/ TU206G 1983 U20606700 thru U20606788 U206G/ TU206G 1984 U20606789 thru U20606846 SEB95-3 Revision 1 Page 8 September 17, 2001 U206G/ TU206G 1985 U20606847 thru U20606920 U206G/ TU206G 1986 U20606921 thru U20607020 207/T207 1969 20700001 thru 20700148 207/T207 1970 20700149 thru 20700190 207/T207 1971 20700191 thru 20700205 207/T207 1972 20700206 thru 20700215 207/T207 1973 20700216 thru 20700227 207/T207 1974 20700228 thru 20700267 207/T207 1975 20700268 thru 20700314 207/T207 1976 20700315 thru 20700362 207A/T207A 1977 20700363 thru 20700414 207A/T207A 1978 20700415 thru 20700482 207A/T207A 1979 20700483 thru 20700562 207A/T207A 1980 20700563 thru 20700654 207A/T207A 1981 20700655 thru 20700729 207A/T207A 1982 20700730 thru 20700762 207A/T207A 1983 20700763 thru 20700767 207A/T207A 1984 20700768 thru 20700788 210 1960 57001 thru 57575 210 618 210A 1961 21057576 thru 21057840 210A 616 210B 1962 21057841 thru 21058085 210C 1963 21058086 thru 21058139 210C 1963 21058141 thru 21058220 A-150L 1972 thru 1973 A-1501001 thru A-1501039 A-A150L 1972 thru 1973 A-A1500001 thru A-A1500009 A182J 1966 A182-0001 thru A182-0056 A182K 1967 A182-0057 thru A182-0096 A182L 1968 A182-0097 thru A182-0116 A182N 1972 A182-0117 thru A182-0136 A182N 1974 A182-0137 thru A182-0146 A182N 1976 A182-0147 thru A182-0148 A-A188B 1972 thru 1976 A-A1880001 thru A-A1880034 F150F 1966 F150-0001 thru F150-0067 F150G 1967 F150-0068 thru F150-0219 F150H 1968 F150-0220 thru F150-0389 F150J 1969 F150-0390 thru F150-0529 F150K 1970 F15000530 thru F15000658 SEB95-3 Revision 1 September 17, 2001 Page 9 F150L 1971 F15000659 thru F15000738 F150L 1972 F15000739 thru F15000863 F150L 1973 F15000864 thru F15001013 F150L 1974 F15001014 thru F15001143 F150M 1975 F15001144 thru F15001248 F150M 1976 F15001249 thru F15001338 F150M 1977 F15001339 thru F15001428 FA150K 1970 FA1500001 thru FA1500081 FA150L 1971 FA1500082 thru FA1500120 FA150L 1972 FA1500121 thru FA1500166 FA150L 1973 FA1500167 thru FA1500211 FA150L 1974 FA1500212 thru FA1500261 FA150M 1975 FA1500262 thru FA1500281 FA150M 1976 FA1500282 thru FA1500311 FA150M 1977 FA1500312 thru FA1500336 FRA150L 1972 FRA1500121 thru FRA1500166 FRA150L 1973 FRA1500167 thru FRA1500211 FRA150L 1974 FRA1500212 thru FRA1500261 FRA150M 1975 FRA1500262 thru FRA1500281 FRA150M 1976 FRA1500282 thru FRA1500311 FRA150M 1977 FRA1500312 thru FRA1500336 F152 1978 F15201429 thru F15201528 F152 1979 F15201529 thru F15201673 F152 1980 F15201674 thru F15201808 F152 1981 F15201809 thru F15201893 F152 1982 F15201894 thru F15201928 F152 1983 F15201929 thru F15201943 F152 1984 F15201944 thru F15201952 F152 1985 F15201953 thru F15201965 F152 1986 F15201966 thru F15201980 FA152 1978 FA1520337 thru FA1520347 FA152 1979 FA1520348 thru FA1520357 FA152 1980 FA1520358 thru FA1520372 FA152 1981 FA1520373 thru FA1520377 FA152 1982 FA1520378 thru FA1520382 FA152 1983 FA1520383 thru FA1520387 FA152 1985 FA1520388 thru FA1520415 FA152 1986 FA1520416 thru FA1520425 FP172 1963 FP172-0001 thru FP172-0003 F172D 1963 F172-0001 thru F172-0018 F172E 1964 F172-0019 thru F172-0085 SEB95-3 Revision 1 Page 10 September 17, 2001 F172F 1965 F172-0086 thru F172-0179 F172G 1966 F172-0180 thru F172-0319 F172H 1967 F172-0320 thru F172-0431 F172H 1967 F172-0436 thru F172-0442 F172H 1967 F172-0444 thru F172-0446 F172H 1968 F172-0432 thru F172-0435 F172H 1968 F172-0443 F172H 1968 F172-0447 thru F172-0559 F172H 1969 F172-0560 thru F172-0654 F172H 1970 F17200655 thru F17200754 F172K 1971 F17200755 thru F17200804 F172L 1972 F17200805 thru F17200904 F172M 1973 F17200905 thru F17201034 F172M 1974 F17201035 thru F17201234 F172M 1975 F17201235 thru F17201384 F172M 1976 F17201385 thru F17201514 F172N 1977 F17201515 thru F17201639 F172N 1978 F17201640 thru F17201749 F172N 1979 F17201750 thru F17201909 F172N 1980 F17201910 thru F17202039 F172P 1981 F17202040 thru F17202134 F172P 1982 F17202135 thru F17202194 F172P 1983 F17202195 thru F17202216 F172P 1984 F17202217 thru F17202233 F172P 1985 F17202234 thru F17202238 F172P 1986 F17202239 thru F17202254 FR172E 1968 FR17200001 thru FR17200060 FR172F 1969 FR17200061 thru FR17200145 FR172G 1970 FR17200146 thru FR17200225 FR172H 1971 FR17200226 thru FR17200275 FR172H 1972 FR17200276 thru FR17200350 FR172J 1973 FR17200351 thru FR17200440 FR172J 1974 FR17200441 thru FR17200530 FR172J 1975 FR17200531 thru FR17200559 FR172J 1976 FR17200560 thru FR17200590 FR172K 1977 FR17200591 thru FR17200620 FR172K 1978 FR17200621 thru FR17200630 FR172K 1979 FR17200631 thru FR17200655 FR172K 1980 FR17200656 thru FR17200665 FR172K 1981 FR17200666 thru FR17200675 F182P 1976 F18200001 thru F18200025 SEB95-3 Revision 1 September 17, 2001 Page 11 F182Q 1977 F18200026 thru F18200064 F182Q 1978 F18200065 thru F18200094 F182Q 1979 F18200095 thru F18200129 F182Q 1980 F18200130 thru F18200169 FR182 1978 FR18200001 thru FR18200020 FR182 1979 FR18200021 thru FR18200045 FR182 1980 FR18200046 thru FR18200070 PURPOSE Service experience indicates the potential for wearing of the flap supports by the flap rollers. To assist in preventing this condition from occurring, a inspection of the flap supports and rollers along with a modification to install stainless steel washers on each side of the forward rollers shall be accomplished. Failure to accomplish this inspection and modification could result in damage to the flap supports and/or loss of flap control. COMPLIANCE Mandatory: A. Initial Inspection Shall be accomplished within the next 100 hours of operation or 12 months, whichever occurs first. NOTE: Compliance with the repetitive inspection of this revision is required if in compliance with the original issue of this service bulletin. B. Repeat Inspection A visual inspection in accordance with Steps 5.B., 8. and 9. of the Accomplishment Instructions, shall be accomplished every 100 hours of operation or 12 months, whichever occurs first. APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design. For Reims Aviation airplanes, DGAC approval has been obtained on technical data in this publication that affects airplane type design. MAN-HOURS Approximately 0.7 man-hours per flap to inspect and install the stainless steel washers. Approximately 4.0 man-hours to install SK180-44 at one flap attach station. SEB95-3 Revision 1 Page 12 September 17, 2001 MATERIAL The following parts are available from Cessna Parts Distribution through an appropriate Cessna Service Station for the suggested list price shown. Part Number Description Qty./Flap Attach Price Station AN3-11A Bolt 1 $ 0.34 (PS) ea. MQ 25 MS21044N3 Nut 2 $ 0.17 (PS) ea. MQ 100 S1450-3S10-032 Washer 2 $ 2.50 (SE) ea. MQ 10 SK180-44-1 Flap Support Rib 1 (if required) $ 122.20 (A) ea. (See Note 1) Assembly And Roller Bearing Replacement Kit SK180-44-2 Left Flap Outboard 1 (if required) $ 178.00 (A) ea. (See Note 2) Support Riders Replacement Kit SK180-44-3 Right Flap Outboard 1 (if required) $ 178.00 (A) ea. (See Note 3) Support Riders Replacement Kit 0523919 Bushing 1 (if required) $ 4.32 (A) ea. (See Note 4) 0523231-5 Bracket (as required) $ 6.61 (SE) ea. (See Note 5) 0523231-24 Bracket (as required) $ 33.00 (SE) ea. (See Note 5) 0523920 Roller Assembly 1 (if required) $ 33.00 (SE) ea. (See Note 4 0523921 Roller Assembly 1 (if required) $ 26.20 (SE) ea. (See Note 4) S1450-5N12-050 Spacer 2 (if required) $ 3.57 (S) ea. MQ 10 (See Note 4) 1220114-1 Spacer 2 (if required) $ 2.48 (SE) ea. (See Note 4) 1220114-2 Spacer 1 (if required) $ 0.35 (PS) ea. MQ 10 (See Note 4) ALL PRICES SUBJECT TO CHANGE WITHOUT NOTICE SEB95-3 Revision 1 September 17, 2001 Page 13 NOTES: 1. This Service Kit will be required if the inspection reveals non-repairable damage to the flap supports. Each SK180-44-1 contains replacement left and right flap supports for one flap attach location, attaching hardware and the hardware required to accomplish the initial modification of installing the S1450-3S10-032 washers. This Service Kit is applicable for all flap attach stations except the outboard flap attach station for airplanes that are equipped with extended length flaps that have three flap attach stations. 2. This Service Kit will be required if the inspection reveals non-repairable damage to the left flap outboard attach station for airplanes equipped with extended length flaps that have three flap attach stations. Each SK180-44-2 contains replacement inboard and outboard flap rider assemblies, attaching hardware and the hardware required to accomplish the initial modification of installing the S1450-3S10-032 washers. 3. This Service Kit will be required if the inspection reveals non-repairable damage to the right flap out board attach station for airplanes equipped with extended length flaps that have three flap assemblies, attaching hardware and the hardware required to accomplish the initial modification of installing the S1450-3S10-032 washers. 4. Refer to the appropriate Illustrated Parts Catalog to determine part applicability. 5. For Model 150, 152, 170, 172 and 175 Series Airplanes, order 0523231-24 Bracket to replace original 0523231-5 Bracket. Refer to applicable Illustrated Parts Catalog for remaining affected airplanes. ACCOMPLISHMENT INSTRUCTIONS Flap Support And Roller Bearing Inspection/Flap Roller Washer Installation Accomplishment Instructions are attached. NOTE: This information shall be considered an amendment to the Cessna Manufacturer's Service/Maintenance Manual or Instructions for continued airworthiness and must be accomplished for ongoing airworthiness compliance as required per 14 CFR Part (FAR) 43.13. CREDIT Not applicable SEB95-3 Revision 1 Page 14 September 17, 2001 OWNER NOTIFICATION A. On March 24, 1995, the following Owner Advisory message was sent to applicable owners of record in SEB95-3A. Dear Cessna Owner, Service experience indicates the potential for wearing of the flap supports by the flap rollers. To assist in preventing this condition from occurring, a inspection of the flap supports and rollers along with a modification to install stainless steel washers on each side of the forward rollers shall be accomplished. Failure to accomplish this inspection and modification could result in damage to the flap supports and/or loss of flap control. Compliance is recommended; should be accomplished within the next 100 hours of operation or 12 months, whichever occurs first. Please contact a Cessna Single Engine Service Station for detailed information regarding the accomplishment of this service bulletin on your airplane. B. On September 17, 2001 the following Owner Advisory message was sent to applicable owners of record in SEB95-3R1A. Dear Cessna Owner: This letter is to provide notification that an inspection is required of the flap supports and rollers on your airplane. Service experience indicates the potential for wearing of the flap supports by the flap rollers. To assist in preventing this condition from occurring, a inspection of the flap supports and rollers along with a modification to install stainless steel washers on each side of the forward rollers shall be accomplished. Failure to accomplish this inspection and modification could result in damage to the flap supports and/or loss of flap control. Compliance is mandatory; A. Initial Inspection Shall be accomplished within the next 100 hours of operation or 12 months, whichever occurs first. NOTE: Compliance with the repetitive inspection of this revision is required if in compliance with the original issue of this service bulletin. B. Repeat Inspection A visual inspection in accordance with Steps 5.B., 8. and 9. of the Accomplishment Instructions, shall be accomplished every 100 hours of operation or 12 months, whichever occurs first. The information contained in the referenced Cessna Service Bulletin shall be considered an amendment to the Cessna Manufacturer's Service/Maintenance Manual or Instructions for continued airworthiness and must be accomplished for ongoing airworthiness compliance as required per 14 CFR Part (FAR) 43.13. Please contact a Cessna Single Engine Service Station for detailed information and make arrangements to have Service Bulletin SEB95-3 Revision 1 accomplished on your airplane. SEB95-3 Revision 1 September 17, 2001 Page 15 ACCOMPLISHMENT Single Engine INSTRUCTIONS A Textron Company SEB95-3 Revision 1 TITLE FLAP SUPPORT AND ROLLER BEARING INSPECTION/FLAP ROLLER WASHER INSTALLATION EFFECTIVITY: MODEL SERIES SERIAL NUMBERS 150 617, 628, 644, 17001 thru 1506469 150 15064971 thru 15079405 A150 A1500001 thru A1500432 A150 A1500434 thru A1500734 A150 15064970 A-150 A-1501001 thru A-1501039 A-A150 A-A1500001 thru A-A1500009 F150 F150-0001 thru FF15001428 FA150 FA1500001 thru FA1500120 FRA152 FRA1500121 thru FRA1500336 152 15279406 thru 15286033 A152 A1520735 thru A1521049 A152 A1500433, 681 F152 F15201429 thru F15201980 FA152 FA1520337 thru FA1520425 170 609, 19401, 20267, thru 27169 172 610, 612, 615, 622, 625, 630, 172 639, 638, 28000 thru 17276654 F172 F172-0001 thru F17202254 R172 R1722000 thru R1723454 R172 P17257189 FR172 FR17200001 thru FR17200675 172RG 691, 172RG0001 thru 172RG1191 P172 P17257120 thru P17257188 FP172 FP172-0001 thru FP172-0003 R172 (T41B/C/D) R172-0001 thru R172-0409 R172(T41D) R1720410 thru R1720620 175 28700A, 55001 thru 17557119, 619 180 604, 614, 624, 645, 30000 thru 18053203 182/T82 613, 631, 634, 675, 33000 thru 18268586 A182 A182-0001 thru A182-0148 R182/TR182 R18200001 thru R18202039 F182 F18200001 thru F18200169 FR182 FR18200001 thru FR18200070 185 632, 652, 185-0001 thru 18504448 188/A188 653, 188-0001 thru 188-0572 188/A188 18800573 thru 18800832 188 18800833 thru 18802348 Original Issue: March 10, 1995 Revision 1: September 17, 2001 Page 1 of 11 To obtain satisfactory results, procedures specified in this publication must be accomplished in accordance with accepted methods and prevailing government regulations. Cessna Aircraft Company cannot be responsible for the quality of work performed in accomplishing the requirements of this publication. Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277, U.S.A. (316) 517-5800 Facsimile (316) 942-9006 COPYRIGHT©1995 ACCOMPLISHMENT INSTRUCTIONS SEB95-3 Revision 1 EFFECTIVITY: (Continued) MODEL SERIES SERIAL NUMBERS A188 678T, 18800833 thru 18803973 A188 18800967T thru 1880974T T188 T18803307T thru T18803974T A-A188 A-A1880001 thru A-A1880034 210-5 (205) 641, 205-0001 thru 205-0480 210-5A (205A) 205-0481 thru 205-0577 206/U206 206-0001 thru 206-0275 U206/TU206 676, U206-0276 thru U20607020 P206/TP206 P206-0001 thru P20600647 207/T207 20700001 thru 20700788 210 616, 618, 57001 thru 21058139 210 21058141 thru 21058220 DESCRIPTION This document provides instructions to inspect the flap supports and attaching structure for damage such as wear, gouges, cracks and security of attachment. APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design. For Reims Aviation airplanes: DGAC approval has been obtained on technical data in this publication that affects airplane type design. REFERENCE SEB95-3R1 CHANGE IN WEIGHT AND BALANCE W EIGHT INCREASE ........................................... Negligible Page 2 ACCOMPLISHMENT INSTRUCTIONS SEB95-3 Revision 1 MATERIAL INFORMATION NOTE: The following components will be required to complete this inspection procedure. Quantities are for each affected flap attach station. PART NUMBER QUANTITY DESCRIPTION AN3-11A 1 Bolt-Forward MS210044N3 2 Nut S1450-3S10-032 2 Washer NOTE: The following kit may be required if the inspection reveals damage to the flap support arm assembly. This kit is not to be installed at the outboard flap attach station for airplanes equipped with extended length flaps (three attach stations). Quantities are for each affected flap station. PART NUMBER QUANTITY DESCRIPTION SK180-44-1 1 Kit, Flap Support and Flap Roller Washer Installation NOTE: The following parts may be required if the inspection reveals wear or damage to the flap attaching parts, rollers or bushings. Refer to the applicable airplane Illustrated Parts Catalog for part applicability, quantity required and location of installation. PART NUMBER QUANTITY DESCRIPTION 0523919 1 Bushing 0523920 1 Roller Assembly 0523921 1 Roller Assembly S1450-5N12-050 2 Spacer 1220114-1 1 Spacer 1220114-2 1 Spacer NOTE: The following kits may also be required if the inspection reveals wear for damage to the flap outboard support riders for airplanes with extended length flaps: PART NUMBER QUANTITY DESCRIPTION SK180-44-2 1 Kit, Left Flap Outboard Support Riders Replacement SK180-44-3 1 Kit, Right Flap Outboard Support Riders Replacement ACCOMPLISHMENT INSTRUCTIONS 1. Attach maintenance warning tags to the cockpit controls within clear view stating: WARNING: MAINTENANCE IN PROGRESS 2. Fully extend the wing flaps. 3. Remove the flaps from the airplane. (Refer to the appropriate airplane Service Manual.) Retain washers, bearings, rollers and aft bolt. Discard forward bolt, aft and forward nut. Page 3 ACCOMPLISHMENT INSTRUCTIONS SEB95-3 Revision 1 4. (Refer to Figure 1, Sheet 4, View A-A, View B-B, and View C-C and Sheet 5, View E-E.) Use a rag damp with Stoddard solvent (or equivalent) and a nonmetallic abrasive pad such as Scotch Brite, clean the flap support arms. NOTE: Complete one flap attach station at a time before moving on to the next. 5. (Refer to Figure 1, Sheet 6, Detail Y.) Using a dye penetrant, inspect each flap support arm or rider at the forward and aft roller assembly mounting points for grooves and/or cracks. NOTE: Circular grooves may have developed from the roller assembly rubbing on the flap support arm or rider. If this condition is present, use an optical or mechanical depth micrometer and measure the depth of the grooves. CAUTION: DO NOT USE POWERED GRINDING DISC OR HAND FILE FOR BLENDING GROOVES. USE CARE WHEN BLENDING GROOVES NOT TO EXCEED 0.020 INCH TOTAL MATERIAL REMOVED. A. If no cracks are present and if any grooves are present, use 400 grit Emery cloth and blend out the grooves using care not to remove excessive material; blending to remove grooves shall not exceed the maximum depth of 0.020 inch. NOTE: Maximum wear and clean-up shall not exceed 0.020 inch material loss. If cracks are present or grooves exceeds a 0.020 inch depth, replace the flap support arms by installing one SK180-44-1 per affected flap station. For airplanes equipped with extended length flaps (Refer to Figure 1, Sheet 3) at the outboard flap attach station, install SK180-44-2 or SK180-44-3 as required. B. Inspect flap track rib assemblies and attaching wing structure for security of attachment, cracks, distortion, loose rivets, corrosion and any other apparent damage. Refer to the appropriate airplane service manual for repair or replacement of any parts as required. C. Apply primer to bare metal and allow one hour to cure. Paint the area to match the flap if desired. 6. (Refer to Figure 1, Sheet 4, View D-D and Sheet 5, View F-F.) Reassemble and install the roller and roller bushing, at both the forward and aft locations, on the flap tracks. NOTE: Before reinstallation of the flaps, inspect the existing attaching parts in all attach locations for wear or damage. If the hardware is worn or damaged, refer to the appropriate airplane Illustrated Parts Catalog and order new attaching parts. Refer to appropriate airplane Service Manual for flap installation. For Model 150, 152, 170, 172 and 175 Series Airplanes, order 0523231-24 Bracket to replace original 0523231-5 Bracket. Refer to applicable parts catalog for remaining affected airplanes. A. Install the two (2) new S1450-3S10-032 washers on the forward roller assembly only, one on each side of the roller bushings, with the square-edge side facing the flap roller assembly, (1) AN3-11A bolt and (1) MS21044N3 nut. Install retained hardware in the aft location using the existing bearing retained in step 3. B. Torque the MS21044N3 nut to 20 inch-pounds. Check the two (2) S1450-3S10-032 washers with finger pressure to assure they will NOT rotate. If rotation is felt, loosen the nut, retorque to 25 inch-pounds and verify the washer cannot be turned with finger pressure. C. Verify the flap roller is free to rotate. 7. Repeat steps 3 thru 6 until all flap supports have been inspected. Page 4 ACCOMPLISHMENT INSTRUCTIONS SEB95-3 Revision 1 8. Operate the flaps full up and full down 3 times. Ensure no binding exists in flap movement. Return flaps to the full up position. Remove maintenance tags. 9. Make an entry in the airplane logbook stating compliance with this service bulletin and method of compliance. Page 5 ACCOMPLISHMENT INSTRUCTIONS SEB95-3 Revision 1 MODEL 152 SHOWN (ALSO APPLIES TO THE SERIALS LISTED BELOW AT THE WING STATIONS SHOWN) 150 617, 628, 644, 649, 17001 Thru 15064969, 15064971 Thru 15079405 A150 A1500001 Thru A1500432 A150 A1500434 Thru A1500734, 15064970 A-150 A-1501001 Thru A-1501039 A-A150 A-A1500001 Thru A-A1500009 F150 F150-0001 Thru F15001428 FA150 FA1500001 Thru FA1500120 FRA150 FRA1500121 Thru FRA1500336 152 15279406 Thru 15286033 A152 681, A1520735 Thru A1521049, A1500433 F152 F16201429 Thru F15201980 FA152 FA1520337 Thru FA1520425 Figure 1. Flap Support Rib Assembly and Roller Bearing Inspection (Sheet 1 of 6) Page 6 ACCOMPLISHMENT INSTRUCTIONS SEB95-3 Revision 1 MODEL 172 SHOWN (ALSO APPLIES TO THE SERIALS LISTED BELOW AT THE WING STATIONS SHOWN) 170 609, 19401, 20267 Thru 27169 R182/ R18200001 Thru R18202039 TR182 172 610, 612, 615, 622, 625, 630, 638, 639, 28000 Thru 17276654 A182 A182-0001 Thru A182-0148 F172 F172-0001 Thru F17202254 F182 F18200001 Thru F18200169 P172 P17257120 Thru P17257188 FR182 FR18200001 Thru FR18200070 R172 R172-0001 Thru R172-0409 185 632, 652, 185-0001 Thru 18504448 (T41 B/C/D) 188/A188 653, 188-0001 Thru 188-0572 R172 R1720410 Thru R1720620 188/A188 18800573 Thru 18800832 (T41D) 188 18800833 Thru 18802348 A188 678T, 18800833 Thru 18803973 R172 R1722000 Thru R1723454, A188 18800967T Thru 18803973T P17257189 T188 T18803307T Thru T 803974T 172RG 691, 172RG0001 Thru 172RG1191 A-A188 A-A1880001 Thru A-A1880034 FP172 FP172-0001 Thru FP172-0003 210-5 (205) 641, 205-0001 Thru 205-0480 210-5A 205-0481 Thru 205-0577 FR172 FR17200001 Thru FR17200675 (205A) 175 28700A, 55001 Thru 17557119, 619 U206 / U20601569 Thru U20607020 TU206 180 604, 614, 624, 645, 30000 Thru 18053203 207/ 20700191 Thru 20700788 T207 182/ 613, 631, 634, 675, T182 33000 Thru 18268586 210 616, 618, 57001 Thru 57575 and 21057576 Thru 21058139 21058141 Thru 21058220 Figure 1. Flap Support Rib Assembly and Roller Bearing Inspection (Sheet 2) Page 7 ACCOMPLISHMENT INSTRUCTIONS SEB95-3 Revision 1 (ALSO APPLIES TO THE SERIALS LISTED BELOW AT THE WING STATIONS SHOWN) 206/U206 206-0001 Thru 206-0275 U206 / 676, U206-0276 Thru U206-1444 and TU206 U20601445 Thru U20601568 P206 / P206-0001 Thru P206-0603 and TP206 P20600604 Thru P20600647 207 / 20700001 Thru 20700190 T207 AIRPLANES WITH EXTENDED FLAPS Figure 1. Flap Support Rib Assembly and Roller Bearing Inspection (Sheet 3) Page 8 ACCOMPLISHMENT INSTRUCTIONS SEB95-3 Revision 1 0523231 FLAP TRACK RIB ASSEMBLY REAR 1221010 FLAP TRACK RIB ASSEMBLY SPAR 2425001 FLAP TRACK RIB ASSEMBLY (REFERENCE) FLAP SPAR 0523901 INSPECT AREAS OF FLAP ROLLER FLAP ASSEMBLY SUPPORT ARM IN CONTACT (REFERENCE) WITH ROLLER ASSEMBLY VIEW A-A VIEW B-B NOTE: DO NOT INSTALL VIEW C-C S1450-3S10-032 WASHERS ON THE AFT ROLLER ASSEMBLY FLAP TRACK (REFERENCE) S1450-3S10-032 (REFERENCE) WASHERFLAP SUPPORT (2 REQUIRED) / ARM FLAP SUPPORT (REFERENCE) ARM MS21044N3 (REFERENCE) NUT (REFERENCE) AN3-11A BOLT NOTE: TORQUE THE MS21044N3 NUT TO (1 REQUIRED) 20 INCH-POUNDS. CHECK THE TWO (2) S1450-3S10-032 WASHERS 0523919 FLAP ROLLER AN960-10 WITH FINGER PRESSURE TO BUSHING WASHER ASSURE THEY WILL NOT ROTATE. (REFERENCE) (1 REQUIRED) IF ROTATION IS FELT, LOOSEN THE 0523921 FLAP ROLLER VIEW D-D NUT, RETORQUE TO 25 INCH- ASSEMBLY POUNDS, AND VERIFY THE (REFERENCE) WASHER CANNOT BE TURNED WITH FINGER PRESSURE Figure 1. Flap Support Rib Assembly and Roller Bearing Inspection (Sheet 4) Page 9 ACCOMPLISHMENT INSTRUCTIONS SEB95-3 Revision 1 REAR 1220058 SPAR FLAP TRACK RIB ASSEMBLY (REFERENCE) FLAP SPAR 1220100 INSPECT AREAS OF FLAP ROLLER FLAP ASSEMBLY SUPPORT ARM IN CONTACT (REFERENCE) WITH ROLLER ASSEMBLY NOTE: DO NOT INSTALL VIEW E-E S1450-3S10-032 WASHERS ON THE AFT ROLLER ASSEMBLY FLAP TRACK (REFERENCE) S1450-3S10-032 WASHER FLAP SUPPORT (2 REQUIRED) ARM FLAP SUPPORT (REFERENCE)ARM ARM (REFERENCE) MS21044N3 NUT (REFERENCE) (1 REQUIRED) NOTE: TORQUE THE MS21044N3 NUT TO 20 INCH-POUNDS. CHECK 0523919 FLAP ROLLER AN960-10 THE TWO (2) S1450-3S10-0 3 2 WASHER WASHERS WITH FINGER (REFERENCE) PRESSURE TO ASSURE THEY 0523921 FLAP ROLLER WILL NOT ROTATE. IF ASSEMBLY ROTATION IS FELT, LOOSEN (REFERENCE) THE NUT, RETORQUE TO 25 INCH-POUNDS AND VERIFY THE WASHER CANNOT BETURNED WITH FINGER PRESSURE Figure 1. Flap Support Rib Assembly and Roller Bearing Inspection (Sheet 5) Page 10 ACCOMPLISHMENT INSTRUCTIONS SEB95-3FLAP SUPPORT Revision 1 ARM (REFERENCE) INSPECT FOR CIRCULAR GROOVES WHICH MAY HAVE DEVELOPED FROM THE ROLLER ASSEMBLY RUBBING ON THE FLAP SUPPORT ARM OR RIDER DETAIL Y FLAP TRACK FLAP SUPPORT (REFERENCE) ARM FLAP SUPPORT (REFERENCE) ARM SUPPORT (REFERENCE) 0.020 INCH MAXIMUM TO INCLUDE CLEAN-UP REPAIR DETAIL Z Figure 1. Flap Support Rib Assembly and Roller Bearing Inspection (Sheet 6) Page 11 Single-Engine SERVICE KIT SK1 80-44 TITLE FLAP SUPPORT AND FLAP ROLLER WASHER INSTALLATION EFFECTIVITY MODEL(S) SERIAL NUMBERS 150 617, 628, 644, 649, 17001 thru 15064969 150 15064971 thru 15079405 A150 A1500001 thru A1500432 A150 A1500434 thru A1500734 A150 15064970 A-150 A-1501001 thru A-1501039 A-A150 A-A1500001 thru A-A1500009 F150 F150-0001 thru F15001428 FA150 FA1500001 thru FA1500120 FRA152 FRA1500121 thru FRA1500336 152 15279406 thru 15286033 A152 681, A1520735 thru A1521049 A152 A1500433 F152 F15201429 thru F15201980 FA152 FA1520337 thru FA1520425 170 609, 19401, 20267 thru 27169 172 610, 612, 615, 622, 625, 630, 639, 638, 28000 thru 17276654 F172 F172-0001 thru F17202254 R172 R1722000 thru R1723454 R172 P17257189 FR172 FR17200001 thru FR17200675 172RG 691,172RG0001 thru 172RG1191 P172 P17257120 thru P17257188 FP172 FP172-0001 thru FP172-0003 R172 (T41B/C/D) R172-0001 thru R172-0409 R172 (T41D) R1720410 thru R1720620 175 28700A, 55001 thru 17557119, 619 180 604, 614, 624, 645, 30000 thru 18053203 182/T182 613, 631,634, 675, 33000 thru 18268586 A182 A182-0001 thru A182-0148 R182/TR182 R18200001 thru R18202039 F182 F18200001 thru F18200169 FR182 FR18200001 thru FR18200070 185 632, 652, 185-0001 thru 18504448 188/A188 653, 188-0001 thru 188-0572 188/A188 18800573 thru 18800832 188 18800833 thru 18802348 A188 678T, 18800833 thru 18803973 A188 18800967T thru 18803973T T188 T18803307T thru T18803974T A-A188 A-A1880001 thru A-A1880034 March 10, 1995 Page 1 of 15 To obtain satisfactory results, procedures specified in this publication must be accomplished in accordance with accepted methods and prevailing government regulations. The Cessna Aircraft Company cannot be responsible for the quality of work performed in accomplishing the requirements of this publication. The Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277, U.S.A. (316) 941-7550, Facsimile (316) 942-9006 COPYRIGHT © 1995 SERVICE KIT SK1 80-44 EFFECTIVITY (Continued) MODEL(S) SERIAL NUMBERS 210-5 (205) 641, 205-0001 thru 205-0480 210-5A (205A) 205-0481 thru 205-0577 206/U206 206-0001 thru 206-0275 U206/TU206 676, U206-0276 thru U20607020 P206/TP206 P206-0001 thru P20600647 207/T207 20700001 thru 20700788 210 616, 618, 57001 thru 21058139 210 21058141 thru 21058220 DESCRIPTION This service kit provides parts and instructions for the removal and installation of the flap support arm rib assembly. APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design. For Reims Aviation airplanes: DGAC approval has been obtained on technical data in this publication that affects airplane type design. REFERENCE SEB95-3 CHANGE IN WEIGHT AND BALANCE MODEL ...................... All WEIGHT INCREASE ............ Negligible. Page 2 SERVICE KIT SK1 80-44 MATERIAL INFORMATION Order one (1) SK180-44-1 Kit per flap attach location except the outboard location of airplanes with extended length flaps (certain Models 206 and 207, refer to Figure 1, Sheet 6 for extended flaps): PART NUMBER QUANTITY DESCRIPTION SK180-44-1 1 Kit, consisting of the following parts: AN3-11A 2 Bolt NAS1149F0363P 1 Washer MS20470AD3-3 50 Rivet MS20470AD3-4 50 Rivet MS20470AD3-5 25 Rivet MS20470AD4-3.5 6 Rivet MS20470AD4-4 6 Rivet MS20470AD4-5 1 Rivet MS21044N3 2 Nut NAS1738B4-1 10 Rivet S1450-3S10-032 2 Washer 0523901-13 1 Rib Assembly-Flap Support Arm Left 0523901-14 1 Rib Assembly-Flap Support Arm Right 1 Instructions Airplanes with extended length flaps order the following kit if required to replace the left flap outboard support riders: PART NUMBER QUANTITY DESCRIPTION SK180-44-2 1 Kit, consisting of the following parts: AN3-11A 1 Bolt MS20470AD4-3.5 6 Rivet MS20470AD4-4 6 Rivet NAS1149F0363P 1 Washer MS21044N3 1 Nut S1450-3S10-032 2 Washer 1220109-1 1 Rider Assembly-Inboard LH 1220109-3 1 Rider Assembly- Outboard LH 1 Instructions Page 3 SERVICE KIT SK1 80-44 MATERIAL INFORMATION (Continued) Airplanes with extended length flaps order the following kit if required to replace the right flap outboard support riders: PART NUMBER QUANTITY DESCRIPTION SK180-44-3 1 Kit, consisting of the following parts: AN3-11A 1 Bolt MS20470AD4-3.5 6 Rivet MS20470AD4-4 6 Rivet MS21044N3 1 Nut NAS1149F0363P 1 Washer S1450-3S10-032 2 Washer 1220109-2 1 Rider Assembly-Inboard RH 1220109-4 1 Rider Assembly- Outboard RH 1 Instructions ACCOMPLISHMENT INSTRUCTIONS 1. Lower the flaps to the full down position and disconnect battery cable and all external power to the airplane. Attach maintenance warning tags, to the battery connector and external power receptacle, stating: WARNING: DO NOT CONNECT ELECTRICAL POWER - MAINTENANCE IN PROGRESS 2. Remove the flaps from the wing. (Refer to the appropriate Service Manual, Flaps - Removal and Installation.) NOTE: As each flap is removed from the wing, all rollers, bushings and spacers will fall free. Retain the forward and aft bearing and bushing and the aft washers for reinstallation. Discard the forward attach bolt, nut and washers and the aft bolt and nut. 3. Drill out rivets securing the upper corrugated flap skin forward edge across the flap spar edge 4 or 5 rivets past the affected flap support station. (Refer to Figure 1, Sheet 1, Detail A.) NOTE: The outboard flap rider assembly replacement on airplanes with three (3) attach point flaps are similar procedures as the inboard and center flap support arm. Refer to Figure 1, Sheet 6, for serial numbers of those airplanes. 4. Drill out rivets securing the upper corrugated flap skin to the flap outboard rib and those rivets securing the trailing edges together enough to be equal to that of step 3. Drill out the rivets securing the flap trailing edge rib from the upper skin, but do not remove the flap trailing edge rib from the lower skin. 5. Roll the corrugated flap skin out of the way toward the center of the flap and secure with a strong reinforced tape. CAUTION: DRILL OFF ONLY ONE FLAP SUPPORT ARM AT A TIME USING THE REMAINING SUPPORT ARM AS A LOCATOR FOR THE NEW SUPPORT ARM INSTALLATION. 6. Drill out the rivets securing the existing left flap support arm to the leading edge skin and the flap spar. Pull the flap support arm through the hole in the leading edge skin and discard the existing flap support arm. (Refer to Figure 1, Sheet 2, Detail B and Sheet 3, Detail C.) Page 4 SERVICE KIT SK1 80-44 CAUTION: IT MAY BE REQUIRED TO TRIM THE LEADING EDGE SKIN AROUND THE FLAP SUPPORT ARMS TO ALLOW CLEARANCE FOR THE FLAP SUPPORT ARMS TO BE REMOVED FROM THE FLAP ASSEMBLY. USE CARE WHEN TRIMMING THE SKIN TO MAINTAIN A MINIMUM OF 0.25 INCH EDGE DISTANCE FROM THE EDGE OF THE SKIN TO THE EDGE OF THE ATTACHING RIVETS. 7. Mark a line down the center of the new 0523901-13 left and 0523901-14 right flap support arm rib flange to aid in aligning the rib with the existing rivet holes of the leading edge skin. 8. Insert the new 0523901-13 left flap support arm in the existing flap support location. Align the aft rivet holes in the flap support arm to the corresponding holes in the flap spar. Secure in position using two temporary metal fasteners. (Refer to Figure 1, Sheet 7, Views A-A, B-B, C-C and Sheet 8, E-E.) 9. Drill the aft holes in the rib assemblies with the holes in the spar using a Number 30 (0.128 inch diameter) drill. Secure each with a temporary metal fastener. 10. Fabricate a spacer using materials on hand (wood, metal, phenolic) that is 2 inches x 5 inches x 0.60 ( + 0.00/-0.01) inch. Lay the removed flap support on the spacer and mark the existing locations of the bolt holes onto the block using a scribe or a pencil. Using a drill press which has been positioned 90° perpendicular to the surface of the spacer, drill two (2) Number 10 (0.193 inch diameter) holes in the spacer at the marked locations. 11. Place the spacer between the two flap support arms. Insert an AN3-11A bolt at the forward hole thru the remaining flap support, the new spacer and the new flap support. Insert another AN3-11A bolt thru the aft position in the same manner. Clamp the spacer and supports midpoint between the bolts with a C-clamp. (Refer to Figure 1, Sheet 9, Detail E, View G-G and Detail D.) 12. Using a 3/32 (0.093 inch diameter) drill, drill eight holes in the rib flange of the flap support rib to the existing rivet locations in the leading edge skin. Use the line made in step 7 to assure alignment. (Refer to Figure 1, Sheet 3, View A-A.) 13. Remove the clamp and spacer. Remove support temporarily and deburr all holes. Touch up parts with primer and allow to cure. 14. Drill out the rivets securing the existing right flap support arm to the leading edge skin and the flap spar. Pull the flap support arm through the hole in the leading edge skin and discard. (Refer to Figure 1, Sheet 2, Detail B and Sheet 3, Detail C.) 15. Insert a new 0523901-14 flap support arm in the existing flap support location. Install the 0523901-13 flap support arm using temporary sheet metal fasteners. Align the aft rivet holes in the 0523901-14 flap support arm to those corresponding holes in the flap spar. Secure into position using a temporary metal fastener. Place the spacer between the two flap support arms and clamp in place with a C- clamp. 16. Using a 3/32 (0.093 inch diameter) drill, drill eight holes into the 0523901-14 rib flange of the flap support rib to the existing rivet locations in the leading edge skin. (Refer to Figure 1, Sheet 3, View A- A.) 17. Remove the C-Clamp and the spacer (retain for other installations if necessary). Remove all temporarily installed parts and deburr all holes. Touch up parts with primer and allow to cure. 18. Secure the new 0523901-13 flap support arm to the leading edge of the flap using MS20470AD3-3 rivets, removing the temporary metal fasteners as required. (Refer to Figure 1, Sheet 2, Detail B, and Sheet 3, Detail C.) 19. Insert the 0523901-14 flap support arm again in the existing flap support location and secure in position using a temporary metal fastener. Secure the aft 3 holes of the rib to the flap spar using MS20470AD4-4 rivets. 20. Secure the rib to the leading edge of the flap using MS20470AD3-4 rivets removing the temporary metal fasteners as required. (Refer to Figure 1, Sheet 2, Detail B, and Sheet 3, Detail C.) Page 5 SERVICE KIT SK1 80-44 21. Reinstall the upper flap skin using MS20470AD3-4 rivets as required, except for the forward position on the aft rib which uses a MS20470AD4-5 rivet. Blind fasteners may be used in the last two positions of the flap ribs if necessary. (Refer to Figure 1, Sheet 2, Detail B and Sheet 3, Detail C.) 22. Reinstall the flap: A. (Refer to Figure 1, Sheet 7, View D-D and Sheet 8, View F-F.) Reassemble and install the roller and roller bushing, at both the forward and aft locations, on the flap tracks. B. Install the two (2) new S1450-3S10-032 washers on the forward roller assembly only, one on each side of the roller bushing, with the square-edge side facing the flap roller assembly, (1) AN3-11A bolt, (1) NAS1149F0363P washer and (1) MS21044N3 nut at each location. NOTE: Install S1450-3S10-032 washers on the forward roller assembly only. Do not install S1450-3S10-032 washers on the aft roller assembly. C. Torque the MS21044N3 nut to 20 inch-pounds. Check the two (2) S1450-3S10-032 washers with finger pressure to assure they will NOT rotate. If rotation is felt, loosen the nut. Retorque to 25 inch-pounds and verify the washer can not be turned with finger pressure. D. Verify the flap roller is free to rotate. E. Remove maintenance warning tags and reconnect battery cable. 23. Operate the flaps full up and full down 3 times. Assure no binding exists in flap movement. Return the flaps to the full up position. 24. Make an entry in the airplane logbook stating this service kit has been installed and the location of the flap attach station that was modified. Page 6 SERVICE KIT SK1 80-44 FLAP CORRUGATED UPPER DETAIL (LEFT FLAP SHOWN, B RIGHT TYPICAL) (MODELS WITH TWO FLAP ATTACH LOCATIONS SHOWN) Figure 1. Flap Support Rib Assembly and Roller Bearing Replacement (Sheet 1 of 9) Page 7 SERVICE KIT SK1 80-44 NOTE: DO NOT INSTALL MS20470AD3-4 RIVET S1450-3S10-032 WASHERS ON (AS REQUIRED TO SECURE THE AFT ROLLER ASSEMBLY RIB TO THE LEADING EDGE SKIN) MS20470AD4-5 RIVET (1 REQUIRED) NAS1738B4-1 RIVET ACCESS PLATE (IF REQUIRED TO SECURE (REFERENCE) M ST AFT TWO POSITIONS RIB TO THE CORRUGATED SKIN) S1450-3S10-032 WASHER (2 REQUIRED) FORWARD ROLLER ASSEMBLY ONLY MS20470AD3-4 RIVET (AS REQUIRED TO SECURE THE SKIN TO FLAP ROLLER THE FLAP STRCTURE) BUSHING (REFERENCE) , - FLAP SPAR (REFERENCE) FLAP ROLLER ASSEMBLY AFT ROLLER (REFERENCE) ATTACH BOLT 0523901-13 LEFT REFER TO STEP 22. FLAP SUPPORT (REFERENCE) S21044N3 RIB ASSEMBLY NUT AN3-11A (1 REQUIRED) (1 REQUIRED) BOLT (1 REQUIRED) 0523901-14 RIGHT FLAP SUPPORT RIB ASSEMBLY (1 REQUIRED) DETAIL B (OUTBOARD ATTACH POSITION) Figure 1. Flap Support Rib Assembly and Roller Bearing Replacement (Sheet 2) Page 8 SERVICE KIT SK1 80-44 NOTE: DO NOT INSTALL ACCESS PLATE MS20470AD3-4 RIVET S1450-3S10-032 WASHERS ON REFERENCE) (AS REQUIRED TO SECURE THE AFT ROLLER ASSEMBLY (1 REQUIRED) RIB TO THE CORRUGATED SKIN) (2 REQUIRED) FORWARD ROLLER ASSEMBLY ONLY FLAP ROLLER BUSHING (REFERENCE) THE FLAP STRUCTURE) FLAP ROLLER ASSEMBLY FLAP SPAR (REFERENCE) (REFERENCE) NUT (1 REQUIRED) REFER TO STEP 22. (1 REQUIRED) (REFERENCE) 0523901-14 BOLT DETAIL C TRIM SKIN AS REQUIRED RIGHT FLAP (1 REQUIRED) (INBOARD ATTACH POSITION) TO REMOVE SUPPORT SUPPORT ARM ASSEMBLY RIB ASSEMBLY MAINTAINING 0.25 INCH (1 REQUIRED) EDGE DISTANCE FLAP SUPPORT RIB ASSEMBLY (REFERENCE) (REFERENCE) DIAMETER) HOLES TO MATCH EXISTING FLAP LEADING /RIVET LOCATIONS IN EDGE SKIN THE FLAP LEADING (REFERENCE) -EDGE SKIN (8 REQUIRED PER RIB) VIEW A-A (REFERENCE) Figure 1. Flap Support Rib Assembly and Roller Bearing Replacement (Sheet 3) Page 9 SERVICE KIT SK1 80-44 Ws 31.75 A _A ws _ 69.875 A A MODEL 152 SHOWN (ALSO APPLIES TO THE SERIALS LISTED BELOW AT THE WING STATIONS SHOWN) 150 617, 628, 644, 649, 17001 Thru 15064969, 15064971 Thru 15079405 A150 A1500001 Thru A1500432 A150 A1500434 Thru A1500734, 15064970 A-150 A-1501001 Thru A-1501039 A-A150 A-A15000001 Thru A-A1500009 F150 F150-0001 Thru F15001428 FA150 FA1500001 Thru FA1500120 FRA150 FRA1500121 Thru FRA1500336 152 15279406 Thru 15286033 A152 681, A1520735 Thru A1521049, A1500433 F152 F15201429 Thru F15201980 FA152 FA1520337 Thru FA1520425 Figure 1. Flap Support Rib Assembly and Roller Bearing Replacement (Sheet 4) Page 10 SERVICE KIT SK1 80-44 WS 39.00 85.875 B B MODEL 172 SHOWN (ALSO APPLIES TO THE SERIALS LISTED BELOW AT THE WING STATIONS SHOWN) 170 609, 19401, 20267 Thru 27169 R182/ R18200001 Thru R18202039 TR182 172 610, 612, 615, 622, 625, 630, 638, 639, 28000 Thru 17276654 A182 A182-0001 Thru A182-0148 F172 F172-0001 Thru F17202254 F182 F18200001 Thru F18200169 P172 P17257120 Thru P17257188 FR182 FR18200001 Thru FR18200070 R172 R172-0001 Thru R172-0409 185 632, 652, 185-0001 Thru 18504448 (T41 B/C/D) 188/A188 653, 188-0001 Thru 188-0572 R172 R1720410 Thru R1720620 188/A188 18800573 Thru 18800832 (T41D) 188 18800833 Thru 18802348 A188 678T, 18800833 Thru 18803973 R172 R1722000 Thru R1723454, A188 18800967T Thru 18803973T P17257189 T188 T18803307T Thru T18803974T 172RG 691, 172RG0001 Thru 172RG1191 A-A188 A-A1880001 Thru A-A1880034 FP172 FP172-0001 Thru FP172-0003 210-5 (205) 641, 205-0001 Thru 205-0480 210-5A 205-0481 Thru 205-0577 FR172 FR17200001 Thru FR17200675 (205A) 175 28700A, 55001 Thru 17557119, 619 U206 / U20601569 Thru U20607020 TU206 180 604, 614, 624, 645, 30000 Thru 18053203 207/ 20700191 Thru 20700788 T207 182/ 613, 631, 634, 675, T182 33000 Thru 18268586 210 616, 618, 57001 Thru 57575 and 21057576 Thru 21058139 21058141 Thru 21058220 Figure 1. Flap Support Rib Assembly and Roller Bearing Replacement (Sheet 5) Page 11 SERVICE KIT SK1 80-44 _ 85.875 MODEL 206 SHOWN (ALSO APPLIES TO THE SERIALS LISTED BELOW AT THE WING STATIONS SHOWN) 206/U206 206-0001 Thru 206-0275 U206 / 676, U206-0276 Thru U206-1444 and TU206 U20601445 Thru U20601568 P206 / P206-0001 Thru P206-0603 and TP206 P20600604 Thr. 20600647 207 / 20700001 Thru 20700190 T207 AIRPLANES WITH EXTENDED FLAPS Figure 1. Flap Support Rib Assembly and Roller Bearing Replacement (Sheet 6) Page 12 SERVICE KIT SK1 80-44 0523231 FLAP TRACK RIB ASSEMBLY WING 1221010 FLAP TRACK RIB ASSEMBLY REAR 2425001 FLAP TRACK RIB ASSEMBLY (REFERENCE) 0523901 AFT FLAP FLAP ASSEMBLY ATTACH POSITION (REFERENCE) FORWARD FLAP (REFERENCE) ATTACH POSITION A A ATTACH POSITION VIEW A-A NOTE: DO NOT INSTALL (REFERENCE) VIEW B-B S1450-3S10-032 WASHERS ON THE AFT ROLLER ASSEMBLY VIEW C-C FLAP TRACK (REFERENCE) S1450-3S10-032 WASHER FLAP SUPPORT LEFT (REFERENCE) FLAP SUPPORT (REFERENCE) ARM (REFERENCE) MS21044N3 NUT AN3-11A (REFERENCE) BOLT (REFERENCE) , NOTE: TORQUE THE MS21044N3 NUT TO 20 INCH-POUNDS. CHECK THE 0523919 FLAP ROLLER NAS1149F0363P TWO (2) S1450-3S10-032 WASHERS BUSHING WASHER WITH FINGER PRESSURE TO (REFERENCE) (1 REQUIRED) ASSURE THEY WILL NOT ROTATE. IF ROTATION IS FELT, LOOSEN THE ASSEMBLY VIEW D-D NUT, RETORQUE TO 25 INCH- POUNDS, AND VERIFY THE WASHER CANNOT BE TURNED WITH FINGER PRESSURE Figure 1. Flap Support Rib Assembly and Roller Bearing Replacement (Sheet 7) Page 13 I SERVICE KIT SK1 80-44 G G E NUMBER 10 (0.1935 INCH DIAMETER) FWD HOLES IN SPACER TO CORRESPOND TO SPACER FORWARD AND AFT ATTACH BOLT HOLE FABRICATE FROM (2 REQUIRED) EXISTING MATERIAL DETAIL D (WOOD, METAL, PHENOLIC) SPACER (REFERENCE) FLAP SUPPORT VIEW G-G ARMS (REFERENCE) NUMBER 10 (0.1935 INCH DIAMETER) HOLES IN SPACER TO CORRESPOND TO FORWARD AND AFT ATTACH BOLT HOLE (REFERENCE) 0.60" MAXIMUM WIDTH DETAIL E Figure 1. Flap Support Rib Assembly and Roller Bearing Replacement (Sheet 9) Page 15