2011-12-01: Equipment/Furnishings

Adoption of the Amendment \n\n\n\tAccordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n0 1. The authority citation for part 39 continues to read as follows: \n\n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n\n\nSec. 39.13 (Amended) \n\n0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2011-12-01 Koito Industries, Ltd: Amendment 39-16708; Docket No. FAA-2010-0857; Directorate Identifier 2010-NM-156-AD. \n\nEffective Date \n\n\n\t(a) This AD is effective August 1, 2011. \n\nAffected ADs \n\n\n\t(b) None. \n\n((Page 31819)) \n\nApplicability \n\n\n\t(c) This AD applies to Koito Industries, Ltd., seats and seating systems having a model number identified in table 1 of this AD that are approved under technical standard order (TSO) TSO-C39b, TSO- C39c, or TSO-C127a, and installed on, but not limited to, airplanes of the manufacturers identified in table 2 of this AD, all type certificated models in any category. \n\n\n\tTable 1--Seat Models ------------------------------------------------------------------------ \n\tModel Nos. ------------------------------------------------------------------------- AFS-105, AFS-136, AFS-235, AFS-315, ARS-183, ARS-189, ARS-190, ARS-200, ARS-242, ARS-242-TA, ARS-254, ARS-255, ARS-263, ARS-276, ARS- \n\t277, ARS-281, ARS-289, ARS-29, ARS-29-03, ARS-304, ARS-308, ARS-311, ARS-311-A, ARS-311-B, ARS-336, ARS(dash)339, \n\tARS-341, ARS-347, ARS-352, ARS-354, ARS-357, ARS-360, ARS-384, ARS-385, \n\tARS-392, ARS(dash)397, ARS-398, ARS-415, ARS-417, ARS-418, ARS-419, ARS-423, ARS-424, ARS-425, \n\tARS(dash)427, ARS(dash)431, ARS-437, ARS-446, ARS-447, ARS-448, ARS- \n\t451, ARS-452, ARS-465, ARS(dash)478, ARS-480, ARS-482, ARS-483, ARS- \n\t493, ARS(dash)494, ARS-507, ARS-510, ARS-511, ARS-514, ARS-516, ARS-518, ARS-527, ARS-542, \n\tARS(dash)543, ARS-550, ARS-552, ARS-553, ARS-554, ARS-571, ARS-574, ARS- \n\t577,ARS(dash)588, ARS-589, ARS-591, ARS-592, ARS-593, ARS-594, ARS- \n\t595, ARS-596, ARS(dash)597, ARS-598, ARS-599, ARS-600, ARS-601, ARS-604, ARS-605, ARS-607, ARS-610, ARS-611, ARS-613, \n\tARS(dash)615, ARS-616, ARS-617, ARS-620, ARS-626, ARS-627, ARS-629, ARS- \n\t636, ARS(dash)641, ARS-642, ARS-643, ARS-644, ARS-646, ARS-647, ARS- \n\t649, ARS-651, ARS-652, ARS-657, ARS-658, ARS-659, ARS-667, ARS-668, ARS- \n\t669, ARS-670, ARS(dash)671, ARS-672, ARS-673, ARS-674, ARS-694, ARS- \n\t697, ARS-704, ARS-707, ARS-709, ARS-710, ARS-813, ARS-814, ARS-815, ARS-823, ARS-831, ARS-832, ARS-833, ARS-835, \n\tARS(dash)836, ARS-837, ARS-838, ARS-840, ARS-841, ARS-843, ARS-844, ARS- \n\t846, ARS(dash)847, ARS-849, ARS-851, ARS-852, ARS-853, ARS-857, ARS- \n\t858, ARS-859, ARS(dash)861, ARS-862, ARS-869, ASS-197D, ASS-215, ASS-30, ASS-30-1, B-317, F11M11, F44A33, P11B31, P11B33, P11M93, P21B33, P21B35, P21B73, P22A23, P32B73, P52B41, P56B63, PB7-2001, T-316, Y11B31, Y11B33, Y11B73, Y15B73, Y21A23, Y21B73, Y27B73, YE1B35, YG7B35, YH1B73, YK2B73 ------------------------------------------------------------------------ \n\n\n\n\n\tTable 2--Affected Airplanes ------------------------------------------------------------------------ \n\tManufacturer Product subtype ------------------------------------------------------------------------ Airbus........................... Transport Airplane. The Boeing Company............... Transport Airplane. McDonnell Douglas Corporation.... Transport Airplane. Mitsubishi Heavy Industries, Ltd. Transport Airplane. Fokker Services B.V.............. Transport Airplane. ------------------------------------------------------------------------ \n\nSubject \n\n\n\t(d) Air Transport Association (ATA) of America Code 25: Equipment/Furnishings. \n\nUnsafe Condition \n\n\n\t(e) This AD results from a determination that the affected seats and seating systems may not meet certain flammability, static strength, and dynamic strength criteria. Failureto meet static and dynamic strength criteria could result in injuries to the flightcrew and passengers during emergency landing conditions. In the event of an in-flight or post-emergency landing fire, failure to meet flammability criteria could result in an accelerated fire. The Federal Aviation Administration is issuing this AD to prevent accelerated fires and injuries to the flightcrew and passengers. \n\nCompliance \n\n\n\t(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. \n\nDetermination of Compliance and Removal \n\n\n\t(g) At the applicable times specified in paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD, determine if the seats and seating systems and their components are compliant with FAA regulations specified in paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD, in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA. For a method to be approved, the approval must specifically refer to this AD. Before re-installing any seat or seating system, modify the existing TSO \n\n((Page 31820)) \n\ntag by defacing the TSO number and letter of designation, e.g., overstrike the TSO identification with an ''X'' (such as ''TSO- C127a'' is defaced to look like (GRAPHIC) (TIFF OMITTED) TR02JN11.012 \n\n\n\n) , and add a tag that specifies non-compliance to the TSO number and letter designation, this AD number, and removal date if applicable. \n\n\n\tNote 1: Determining if the seats and seating systems and their components are compliant may be done by independent re-qualification of the affected TSO article that has thorough control of the design and production process. \n\n\n\n\n\tNote 2: Components of seats and seating systems include any non- metallic exposed part, assembly, or item. A component can include a seat cushion, recline cable, hook and loop (hook and loop is a generic term for Velcro), anda leather cover that is glued to a seat, headrest, or arm cap. \n\n\n\t(1) For Koito Industries, Ltd., seats approved under TSO-C39b or TSO-C39c: Within 2 years after the effective date of this AD, determine if the seats are compliant with 14 CFR 25.561(b)(3)(ii) and 14 CFR 25.561(b)(3)(iii) at the level that the TSO was issued and determine if seats exhibit sharp or injurious surfaces. If any seats are not shown to be compliant with 14 CFR 25.561(b)(3)(ii) and 14 CFR 25.561(b)(3)(iii), or if any seats are shown to exhibit sharp or injurious surfaces in testing conducted to satisfy the original TSO authorization program or subsequent verification tests required by this paragraph, within 2 years after the effective date of this AD, remove the non-compliant seats. \n\t(2) For Koito Industries, Ltd., seating systems approved under TSO-C127a: Within 2 years after the effective date of this AD, determine if the seating systems are compliant with either of the regulations specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD and determine if seating systems exhibit sharp or injurious surfaces. If any seating systems are not shown to be compliant with either of the regulations specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, or if any seating systems are shown to exhibit sharp or injurious surfaces in testing conducted to satisfy the original TSO authorization program or subsequent verification tests required by this paragraph, within 2 years after the effective date of this AD, remove the non-compliant seating systems, except as provided by paragraph (h) of this AD. \n\t(i) 14 CFR 25.561(b)(3)(ii) and 14 CFR 25.561(b)(3)(iii). \n\t(ii) 14 CFR 25.562(b)(2), and 14 CFR 25.562(c)(7). \n\t(3) For Koito Industries, Ltd., seating systems approved under TSO-C127a that are shown to be compliant with 14 CFR 25.561(b)(3)(ii) and 14 CFR 25.561(b)(3)(iii) and that are shown to not exhibit sharp or injurious surfaces during the actions required by paragraph (g)(2) or (h)(2) of this AD: Within 6 years after the effective date of this AD, determine if the seating systems are compliant with 14 CFR 25.562(b)(2), and 14 CFR 25.562(c)(7) and determine if seating systems exhibit sharp or injurious surfaces. If any seating systems are not shown to be compliant with 14 CFR 25.562(b)(2), and 14 CFR 25.562(c)(7), or if any seating systems are shown to exhibit sharp or injurious surfaces in testing conducted to satisfy the original TSO authorization program or subsequent verification tests required by this paragraph, within 6 years after the effective date of this AD, remove the non-compliant seating systems. \n\t(4) For components of Koito Industries, Ltd., seats approved under TSO-C39b or TSO-C39c and components of seating systems approved under TSO-C127a: Within 3 years after the effective date of this AD, determine if the seat bottom cushion assembly and seat back cushion assembly are shown to be compliant with 14 CFR 25.853(c). If any seat bottom or seat backcushion assembly is not shown to be compliant with 14 CFR 25.853(c), within 3 years after the effective date of this AD, remove the non-compliant seat bottom and or seat back cushion assembly. If a seat cushion is replaced on airplanes required to meet 14 CFR 25.562 requirements (either by their original certification basis or post-type certificate modifications), the replacement seat cushion must have consistent seat bottom stiffness and seat reference point locations using the guidance found in paragraph 9 of Appendix 3 of FAA Advisory Circular 25.562-1B, dated January 10, 2006 (http://rgl.faa.gov/Regulatory-- and--Guidance--Library/rgAdvisoryCircular.nsf/0/ 808324bf7790fda3862571010075bcbf/$FILE/AC25.562-1b.pdf); however, compliance with 14 CFR 25.562(c)(2), i.e. lumbar load, does not need to be shown. \n\t(h) For seating systems that are shown to be compliant with the regulations specified in paragraph (g)(2)(ii) of this AD, but are shown to exhibit sharp or injurious surfaces during the tests required to show compliance with paragraph (g)(2)(ii) of this AD: Do the actions specified in paragraph (h)(1) or (h)(2) of this AD using a method approved in accordance with the procedures specified in paragraph (l) of this AD. \n\t(1) Within 2 years after the effective date of this AD: Remove the non-compliant seating systems. \n\t(2) Within 2 years after the effective date of this AD: Determine if the seating systems are compliant with the regulations specified in paragraph (g)(2)(i) of this AD, and determine if the seating systems exhibit sharp or injurious surfaces during the tests required to show compliance with paragraph (g)(2)(i) of this AD. If any seating systems are not shown to be compliant with the regulations specified in paragraph (g)(2)(i) of this AD, or if any seating systems are shown to exhibit sharp or injurious surfaces in testing conducted to satisfy the original TSO authorization program or subsequent verification tests required by this paragraph, within 2 years after the effective date of this AD, remove the non- compliant seating systems. \n\n\n\tNote 3: For airplanes not required to comply with any 14 CFR 25.562 requirements in either original certification basis or post- type certificate modifications, the use of an FAA Part 21 Production Approval Holder to develop and conduct the test program (in accordance with their procedures, including the control and oversight of the test facility) will facilitate the FAA approval process. \n\n\n\n\n\tNote 4: For airplanes not required to comply with any 14 CFR 25.562 requirements in either original certification basis or post- type certificate modifications, the use of a new-build test article is acceptable for static testing. \n\n\n\n\n\tNote 5: For airplanes not required to comply with any 14 CFR 25.562 requirements in either original certification basis or post- type certificate modifications, conformity inspections of test articles consisting of a seat from the fleet (or from spares), should confirm aspects such as matching the seat part number to that noted in the test plan, noting the general condition of the seat, noting revisions/modifications that have been made to the seat (typically noted on modification placards), and verifying the date of manufacture. \n\n\n\n\n\tNote 6: For all airplanes, it is not required to test all in- service seat part numbers. The use of similarity is acceptable to show that the results obtained from a chosen test article are valid for other seat part numbers. Koito Interface Loads Reports/drawings may be used as a source of guidance for input data for the similarity analysis. The similarity methodology must be agreed on using the procedures specified in paragraph (l) of this AD. For airplanes required to comply with any 14 CFR 25.562 requirements in either original certification basis or post-type certificate modifications, the similarity methodology does not necessarily need to follow all guidelines as given in FAA AC 25.562-1B (http:// rgl.faa.gov/Regulatory--and--Guidance--Library/ rgAdvisoryCircular.nsf/0/808324bf7790fda3862571010075bcbf/$FILE/ AC25.562-1b.pdf). However, it must be agreed on using the procedures specified in paragraph (l) of this AD. \n\n\n\n\n\tNote 7: For airplanes required to comply with any 14 CFR 25.562 requirements in either original certification basis or post-type certificate modifications, the use of an FAA Part 21 Production Approval Holder to develop and conduct the test program (in accordance with their procedures, including the control and oversight of the test facility) will facilitate the FAA approval process. \n\n\n\n\n\tNote 8: For airplanes required to comply with any 14 CFR 25.562 requirements in either original certification basis or post-type certificate modifications, the use of a new-build test article is acceptable for static testing. However, in order to account for unknown production non-conformities, test articles for dynamic testing must be seats removed from serviceor spare seats delivered at the same time as the aircraft, unless newly produced test articles are shown to conform with in-service seats. \n\n\n\n\n\tNote 9: For airplanes required to comply with any 14 CFR 25.562 requirements in either original certification basis or post-type certificate modifications, conformity checks of test articles consisting of a seat from the fleet (or from spares) should confirm aspects such as matching the seat part number to that \n\n((Page 31821)) \n\nnoted in the test plan, noting the general condition of the seat, noting revisions/modifications that have been made to the seat (typically noted on modification placards), and verifying the date of manufacture. \n\n\n\n\n\tNote 10: Regarding 14 CFR 25.853(c), in order to account for unknown production non-conformities, test articles should be constructed from in-service cushions. The guidance in FAA AC 25.853- 1 (http://rgl.faa.gov/Regulatory--and--Guidance--Library/ rgAdvisoryCircular.nsf/0/7f0b93c640a3ae48862569d100732cfe/$FILE/ ATT9758X/AC25.853-1.pdf) is applicable. However, it may also be acceptable to test brand new test specimens, provided that it is shown that the in-service cushions consist of foams/covers which were supplied to Koito and marked by a different production organization approved in the FAA and/or EASA system. Test reports issued by any qualified design organization acceptable to the FAA will be acceptable; after May 23, 2011, any tests performed in the Koito seat cushion oil burner test facility, under JCAB supervision, will be acceptable. An independent approval of the seat cushion, such as a TSO-C72 (individual floatation device) may be sufficient to show compliance. \n\nParts Installation: Seats and Seating Systems \n\n\n\t(i) As of the effective date of this AD, no person may install on any airplane any Koito Industries, Ltd., seat and seating system having any model number identified in table 1 of this AD that are approved under TSO-C39b, TSO-C39c, or TSO-C127a; unless it is shown to meet applicable airworthiness requirements, except as specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD. \n\t(1) Seats and seating systems may be removed from service and re-installed on airplanes operated by the same operator. \n\t(2) New seats and seating systems may be installed as direct spares for the same part number seats or seating systems. \n\n\n\tNote 11: A ''direct'' spare has the same part number of the part it replaces. \n\n\n\t(3) Seats and seating systems installed as direct spares are subject to the applicable requirements and compliance times specified in this AD. \n\nParts Installation: Installation and Re-arrangement \n\n\n\t(j) Installation of seats and seating systems other than those installed as direct spares, as specified in paragraph (i) of this AD, is considered a new installation that needs approval and must comply with all regulations, except that re-arrangement of the existing installed seats on an airplane is acceptable following the same installation instructions and limitations as the original certification (e.g., if the original limitations allowed 32'' to 34'' pitch, the new layout must be pitched within that range). \n\nParts Installation: Components of Seats and Seating Systems \n\n\n\t(k) As of the effective date of this AD, no person may install on any airplane any component of any seat or seating system having any model number identified in table 1 of this AD that is approved under TSO-C39b, TSO-C39c, or TSO-C127a, unless the component is shown to meet the applicable airworthiness requirements; except as specified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD. \n\t(1) Components specified in paragraph (g)(4) of this AD may be removed from service and re-installed on airplanes operated by the same operator. \n\t(2) New components may be installed as direct spares for the same part number components. \n\t(3) Components specified in paragraph (g)(4) of this AD that are installed as direct sparesare subject to the applicable requirements and compliance times specified in paragraph (g)(4) of this AD. \n\nAlternative Methods of Compliance (AMOCs) \n\n\n\t(l)(1) The Manager, Los Angeles ACO, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. \n\t(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. \n\nRelated Information \n\n\n\t(m) For more information about this AD, contact Patrick Farina, Aerospace Engineer, Cabin Safety Branch, ANM-150L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712-4137; phone: 562-627-5344; fax: 562-627- 5210; e-mail: Patrick.Farina@faa.gov. \n\nMaterial Incorporated by Reference \n\n\n\t(n) None.