AD 2004-19-01

The FAA adopts a new airworthiness directive (AD) that will supersede AD 86-26-04, which applies to certain Cessna Aircraft Company (Cessna) 120, 140, 140A, 150, F150, 170, 172, F172, FR172, P172D, 175, 177, 180, 182, 185, A185E, 190, 195, 205, 205A, 206, P206, P206E, TP206A, TU206, TU206E, U206, U206E, 207, T207, 210, T210, 336, 337, and T337 series airplanes. AD 86-26-04 currently requires you to inspect and, if necessary, modify the pilot/co-pilot upper shoulder harness adjusters that have certain Cessna accessory kits incorporated. This AD is the result of reports that additional airplanes have the same unsafe condition and the manufacturer revised the service information to add these airplanes and correct the part number of the shoulder harness adjusters. Consequently, this AD retains the actions of 86-26-04, adds additional airplanes to the applicability section of this AD, and incorporates the revised service information. We are issuing this AD to prevent slippage of the pilot/co-pilot shoulder harness, which could result in failure of the shoulder harness to maintain proper belt length adjustment and tension. Such failure could result in pilot/co- pilot injury.

Final rule.

2004-19-01 Cessna Aircraft Company: Amendment 39-13795; Docket No. 2003-CE-40-AD; Supersedes AD 86-26-04, Amendment 39-5503. \n\nWhen Does This AD Become Effective? \n\n\t(a) This AD becomes effective on November 1, 2004. \n\nWhat Other ADs Are Affected by This Action? \n\n\t(b) This AD supersedes AD 86-26-04, Amendment 39-5503. \n\nWhat Airplanes Are Affected by This AD? \n\n\t(c) This AD affects the following airplane models and serial numbers that are certificated in any category and incorporate one of the Cessna accessory kits specified in paragraph (d) of this AD. \n\n\n\nModel \nSerial number \n(1) 120\n8000 through 15075. \n(2) 140 \n8000 through 15075. \n(3) 140A\n15200 through 15724. \n(4) 150\n617, 17001 through 17999, and 59001 through 59018. \n(5) 150A \n628 and 15059019 through 15059350. \n(6) 150B \n15059351 through 15059700. \n(7) 150C\n15059701 through 15060087. \n(8) 150D\n15060088 through 15060772. \n(9) 150E \n644 and 15060773 through 15061532. \n(10) 150F\n15061533through 15064532. \n(11) 150G\n15064533 through 15064969 and 15064971 through 15067198. \n(12) 150H\n649 and 15067199 through 15069308. \n(13) 150J\n15069309 through 15071128. \n(14) 150K\n15071129 through 15072003. \n(15) 170\n18000 through 18729. \n(16) 170A \n18730 through 19400 and 19402 through 20266. \n(17) 170B\n20267 through 20999 and 25000 through 27169. \n(18) 172\n610, 612, 615, 28000 through 29999, 36000 through 36999, and 46001 through 46754. \n(19) 172A \n622, 625, and 46755 through 47746. \n(20) 172B\n630 and 17247747 through 17248734. \n(21) 172C\n17248735 through 17249544. \n(22) 172D\n17249545 through 17250572. \n(23) 172E \n639 and 17250573 through 17251822. \n(24) 172F \n17251823 through 17253392. \n(25) 172G\n17253393 through 17254892. \n(26) 172H\n638, 17254893 through 17256492, and 17256494 through 17256512. \n(27) 172I \n17256513 through 17257161. \n(28) 172K\n17257162 through 17258486 and 17258487 through 17259223. \n(29) P172D \nP17257120 through P17257188.(30) 175\n626, 640, 28700A, and 55001 through 56238. \n(31) 175A\n619 and 56239 through 56777. \n(32) 175B\n17556778 through 17557002. \n(33) 175C\n17557003 through 17557119. \n\n\n(34) 177 \n661, 17700001, and 17700003 through 17701164. \n(35) 177A \n17701165 through 17701370. \n(36) 177B \n17701371 through 17701471 and 17701473 through 17701530. \n(37) 180 \n604, 614, 30000 through 32661. \n(38) 180A\n32662 through 32999 and 50001 through 50355. \n(39) 180B \n50356 through 50661. \n(40) 180C \n624 and 50662 through 50911. \n(41) 180D \n18050912 through 18051063. \n(42) 180E\n18051064 through 18051183. \n(43) 180F \n18051184 through 18051312. \n(44) 180G \n18051313 through 18051445. \n(45) 180H \n18051446 through 18052175. \n(46) 182 \n613 and 33000 through 33842. \n(47) 182A \n33843 through 34753, 34755 through 34999, and 51001 through 51556. \n(48) 182B\n34754, 51557 through 51622, and 51624 through 52358. \n(49) 182C \n631 and 52359 through 53007. \n(50) 182D \n51623 and 18253008through 18253598. \n(51) 182E \n18253599 through 18254423. \n(52) 182F\n18254424 through 18255058. \n(53) 182G\n18255059 through 18255844. \n(54) 182H\n634 and 18255846 through 18256684. \n(55) 182J\n18256685 through 18257625. \n(56) 182K \n18255845, 18257626 through 18257698, and 18257700 through 18258505. \n(57) 182L \n18258506 through 18259305. \n(58) 182M \n662, 18257699, and 18259306 through 18260055. \n\n\n(59) 182N\n18260056 through 18260445. \n(60) 185\n632 and 185-0001 through 185-0237. \n(61) 185A\n185-0238 through 185-0512. \n(62) 185B \n185-0513 through 185-0653. \n(63) 185C \n185-0654 through 185-0776. \n(64) 185D \n185-0777 through 185-0967. \n(65) 185E \n185-0968 through 185-1149. \n(66) A185E \n185-0968 through 185-1599 and 18501600 through 18501832 \n(67) 190\n7001 through 7999 and 16000 through 16183. \n(68) 195 \n7001 through 7999 and 16000 through 16183. \n(69) 206\n206-0001 through 206-0275. \n(70) P206 \nP206-0001 through P206-0160. \n(71) P206A \nP206-0161 through P206-0306. \n(72) P206B\nP206-0307 through P206-0419. \n(73) P206C \nP206-0420 through P206-0519. \n(74) P206D\nP206-0520 through P206-0603. \n(75) P206E\nP20600604 through P20600647. \n(76) U206 \nU206-0276 through U206-0437. \n(77) U206A \nU206-0438 through U206-0656. \n(78) U206B\nU206-0657 through U206-0914. \n(79) U206C \nU206-0915 through U206-1234. \n(80) U206D \nU206-1235 through U206-1444 and U20601445 through U20601587. \n(81) TP206A \nP206-0161 through P206-0306. \n(82) TP206B\nP206-0307 through P206-0419. \n(83) TP206C\nP206-0420 through P206-0519. \n(84) TP206D \nP206-0520 through P206-0603. \n(85) TP206E\nP20600604 through P20600647. \n(86) TU206A\nU206-0487 through U206-0656. \n(87) TU206B\nU206-0657 through U206-0914. \n(88) TU206C \nU206-0915 through U206-1234. \n(89) TU206D\nU206-1235 through U206-1444 and U20601445 through U20601587. \n(90) 207\n20700001 through 20700190. \n(91) T207 \n20700001 through 20700190. \n(92) 210 \n618 and 57001 through 57575. \n(93) 210-5 (205) \n641, 648, and 205-0001 through 205-0480. \n(94) 210-5 (205A) \n205-0481 through 205-0577. \n(95) 210A \n616 and 21057576 through 21057840. \n(96) 210B\n21057841 through 21058085. \n(97) 210C\n21058086 through 21058139 and 21058141 through 21058220. \n(98) 210D\n21058221 through 21058510. \n(99) 210E \n21058511 through 21058715. \n(100) 210F \n21058716 through 21058818. \n(101) 210G\n21058819 through 21058936. \n(102) 210H\n21058937 through 21059061. \n(103) 210J \n21059062 through 21059199. \n(104) 210K \n21059200 through 21059351. \n(105) T210F\nT210-0001 through T210-0197. \n(106) T210G \nT210-0198 through T210-0307. \n(107) T210H \nT210-0308 through T210-0392. \n(108) T210J\nT210-0393 through T210-0454. \n(109) T210K\n21059200 through 21059351. \n(110) F150G\nF150-0068 through F150-0219. \n(111) F150H \nF150-0220 through F150-0389. \n(112) F150J \nF150-0390 through F150-0529. \n(113) F150K \nF15000530 through F15000658. \n(114) F172D \nF172-0001 through F172-0018. \n(115)F172E\nF172-0019 through F172-0085. \n(116) F172F \nF172-0086 through F172-0179. \n(117) F172G\nF172-0180 through F172-0319. \n(118) F172H \nF172-0320 through F172-0654 and F17200655 through F17200754. \n(119) FR172E \nFR17200001 through FR17200060. \n(120) FR172F\nFR17200061 through FR17200145. \n(121) FR172G\nFR17200146 through FR17200225. \n(122) 336 \n633, 636, and 336-0001 through 336-0195. \n(123) 337 \n647 and 337-0002 through 337-0239. \n(124) 337A \n337-0240 through 337-0305, 337-0307 through 337-0469, and 337-0471 through 337-0525. \n(125) 337B \n656, 337-0001, 337-0470, 337-0526 through 337-0568, and 337-0570 through 337-0755. \n(126) 337C\n337-0756 through 337-0978. \n(127) 337D\n337-0979 through 337-1193. \n(128) 337E\n33701194 through 33701316. \n(129) T337B\n337-0001, 337-0470, 337-0526 through 337-0568, and 337-0570 through 337-0755. \n(130) T337C\n337-0756 through 337-0978. \n(131) T337D \n337-0979 through 337-1193. \n(132) T337E\n33701194 through 33701316. \n\nWhat Cessna Accessory Kits Are Affected by This AD? \n\n\t(d) The following is a list of the affected Cessna accessory kits: \n\t\n\nCessna Accessory Kit\nAK140-10 \nAK150-7 \nAK150-121 \nAK170-10 \nAK177-10 \nAK182-75 \nAK195-10 \nAK210-77 \nAK210-93 \nAK210-171 \nAK210-172 \nAK210-173 \nAK210-174 \nAK336-32 \nAK336-36 \nAK336-103 \n\n\n\n\tNote: Retainer springs, part number (P/N) 443030-401, used in Cessna service kits are not affected by this AD. \n\nWhat Is the Unsafe Condition Presented in This AD? \n\n\t(e) The actions specified in this AD are intended to prevent slippage of the pilot/co-pilot shoulder harness, which could result in failure of the shoulder harness to maintain proper belt length adjustment and tension. This failure could result in pilot/co-pilot injury. \n\nWhat Must I Do To Address This Problem? \n\n\t(f) To address this problem, you must do the following: \n\n\n\nActions\nCompliance \nProcedures\n(1) Inspect only the upper shoulder harness adjuster (part number (P/N) 443030-401) for the presence of a retainer spring. \nWithin the next 25 hours time-in-service (TIS) after November 1, 2004 (the effective date of this AD). \nFollow Cessna Single Engine Service Bulletin SEB86-8, Revision 1, and Cessna Multi-engine Service Bulletin MEB86-22, Revision 1, both dated July 28, 2003. \n(2) If a retainer spring is found during the inspection of the upper shoulder harness adjuster (P/N 443030-401) required in paragraph (f)(1) of this AD: (i) Remove the spring by cutting each side; and \n(ii) stamp out the -401 identification number. \nPrior to further flight after the inspection required in paragraph (f)(1) of this AD. \nFollow Cessna Single Engine Service Bulletin SEB86-8, Revision 1, and Cessna Multi-engine Service Bulletin MEB86-22, Revision 1, both dated July 28, 2003. \n(3) If a retainer spring is not found during the inspection of the upper shoulder harness adjuster (P/N 443030-401) required in paragraph (f)(1) of this AD, make an entry in the airplane log book showing compliance with this AD. \nPrior to further flight after the inspection required in paragraph (f)(1) of this AD. \nFollow Cessna Single Engine Service Bulletin SEB86-8, Revision 1, and Cessna Multi-engine Service Bulletin MEB86-22, Revision 1, both dated July 28, 2003. \n(4) Only incorporate Cessna Accessory Kits identified in paragraph (d) of this AD that have been inspected and modified in accordance with paragraphs (f)(1), (f)(2), (f)(2)(i), and (f)(2)(ii) of this AD. \nAs of November 1, 2004 (the effective date of this AD). \nFollow Cessna Single Engine Service Bulletin SEB86-8, Revision 1, and Cessna Multi-engine Service bulletin MEB86-22, Revision 1, both dated July 28, 2003. \n\n\n\t(g) If you did the actions of this AD using Cessna Single Engine Service Bulletin SEB86-8 and Cessna Multi-engine Service Bulletin MEB86-22, both dated November 21, 1986, no further action is required as long as you used shoulder harness adjuster, P/N 443030- 401. \n\nMay I Request an Alternative Method of Compliance? \n\n\t(h) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Wichita Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance, contact Gary D. Park, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4123; facsimile: (316) 946-4107. \n\nDoes This AD Incorporate Any Material by Reference? \n\n\t(i) You must do the actions required by this AD following the instructions in Cessna Single Engine Service Bulletin SEB86-8, Revision 1, and Cessna Multi-engine Service Bulletin MEB86-22, Revision 1, both dated July 28, 2003. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You may get a copy from Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 942-9006. You may review copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Discussion \n\n\tWhat is the background of the subject matter? Cessna designed add- on shoulder harness assembly accessory kits for the pilot/co-pilot seats for certain Cessna airplanes. These shoulder harness assemblies incorporate a retainer spring in the adjuster on the upper and lower shoulder harness. The retainer spring may have been inadvertently installed on the belt friction pin. This installation of the spring in the upper shoulder harness adjuster will not allow the belt webbing to lock in place. \n\n\tThis caused us to issue AD 86-26-04, Amendment 39-5503 (52 FR 520, January 7, 1987). AD 86-26-04 currently requires the following on certain Cessna 120, 140, 140A, 150, F150, 170, 172, F172, FR172, P172D, 175, 177, 180, 182, 185, A185E, 190, 195, 205, 205A, 206, P206, P206E, TP206A, TU206, TU206E, U206, U206E, 207, T207, 210, T210, 336, 337, and T337 series airplanes: \n\n--Inspecting the upper shoulder harness adjuster for the presence of a retainer spring; \n--If a retainer spring is found, removing the retainer spring; and \n--Stamping out the -401 identification number. \n\n\tWhat has happened since AD 86-26-04 to initiate this action? We have received reports that additional airplanes have the same unsafe condition. Cessna has revised the related service information to include these additional airplanes. \n\n\tCessna also revised the service information to correct the reference to the part number (P/N) of the shoulder harness adjusters. The P/N is referenced as 44030-401 in Cessna Single Engine Service Bulletin SEB86-8 and Cessna Multi-engine Service Bulletin MEB86-22, both dated November 21, 1986. The correct P/N is 443030-401. \n\n\tWhat is the potential impact if FAA took no action? If not corrected, the shoulder harness could fail to maintain proper belt length adjustment and tension. Such failure could result in pilot/co-pilot injury. \n\n\tHas FAA taken any action to this point? We issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to certain Cessna Models 120, 140, 140A, 150, F150, 170, 172, F172, FR172, P172D, 175, 177, 180, 182, 185, A185E, 190, 195, 206, P206, U206, TP206, TU206, 207, T207, 210, T210, 336, 337, and T337 series airplanes. This proposal was published in the Federal Register as a supplemental notice of proposed rulemaking (NPRM) on February 27, 2004 (69 FR 9277). The supplemental NPRM proposed to supersede AD 86-26-04 with a new AD that would require you to: \n\n--Inspect the upper shoulder harness adjuster for the presence of a retainer spring; \n--If a retainer spring is found, remove the retainer spring; and \n--Stamp out the -401 identification number. \n\n\tWas the public invited to comment? The FAA encouraged interested persons to participate in the making of this amendment. The following presents the comment received on the proposal and FAA's response to the comment: \n\nComment Issue: Clarify Whether Retainer Springs, Part Number (P/N) 443030-401, Used in Cessna Service Kits Are Affected by This AD \n\n\tWhat is the commenter's concern? The commenter states that there is confusion about whether retainer springs, P/N 443030-401, used in Cessna service kits are affected by this AD. The commenter states that the service kits are different and unrelated to the shoulder harness assembly accessory kits referenced in the AD. The commenter believes this is confusing and may result in a mechanic cutting the spring on the service kit adjusters in an effort to comply with this AD. \n\n\tThe commenter wants us to put a note in the AD to clarify that Cessna service kits that incorporate the use of P/N 443030-401 are not affected by this AD. \n\n\tWhat is FAA's response to the concern? We concur with the commenter and will add a paragraph in the AD for clarification. We will change the final rule AD action based on this comment. \n\nConclusion \n\n\tWhat is FAA's final determination on this issue? We carefully reviewed all available information related to the subject presented above and determined that air safety and the public interest require the adoption of the rule as proposed except for the changes discussed above and minor editorial corrections. We have determined that these changes and minor corrections: \n\n--Provide the intent that was proposed in the NPRM for correcting the unsafe condition; and \n--Do not add any additional burden upon the public than was already proposed in the NPRM. \n\nChanges to 14 CFR Part 39--Effect on the AD \n\n\tHow does the revision to 14 CFR part 39 affect this AD? On July 10, 2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which governs the FAA's AD system. This regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. This material previously was included in each individual AD. Since this material is included in 14 CFR part 39, we will notinclude it in future AD actions. \n\nCosts of Compliance \n\n\tHow many airplanes does this AD impact? We estimate that this AD affects 75,329 airplanes in the U.S. registry. \n\n\tWhat is the cost impact of this AD on owners/operators of the affected airplanes? We estimate the following costs to accomplish the inspection: \n\n\nLabor cost\nParts cost\nTotal cost airplane\nTotal cost on U.S. operators\n1 workhour x $65 per hour = $65\nNo parts required\n$65\n$65 x 75,329 = $4,896,385\n\n\n\tWe estimate the following costs to accomplish any necessary modification that will be required based on the results of this inspection. We have no way of determining the number of airplanes that may need this modification: \n\n\n\nLabor cost\nParts cost\nTotal cost per airplane\n1 workhour x $65 per hour = $65\nNo parts required\n$65\n\n\n\tWhat is the difference between the cost impact of this AD and the cost impact of AD 86-26-04? The difference is the addition of 26 airplanes to the applicability section of this AD. There is no difference in cost to perform the inspection and the modification. \n\nRegulatory Findings \n\n\tWill this AD impact various entities? We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. \n\n\tWill this AD involve a significant rule or regulatory action? For the reasons discussed above, I certify that this AD: \n\n\t1. Is not a "significant regulatory action" under Executive Order 12866; \n\n\t2. Is not a "significant rule" under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and \n\n\t3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. \n\n\tWe prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include "AD Docket No. 2003-CE-40-AD" in your request. \n\nList of Subjects in 14 CFR Part 39 \n\n\tAir transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. \n\nAdoption of the Amendment \n\nAccordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n1. The authority citation for part 39 continues to read as follows: \n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n§ 39.13 (Amended) \n\n2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 86-26-04, Amendment 39-5503 (52 FR 520, January 7, 1987), and by adding a new AD to read as follows: