A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Boeing Model 737-100, - 200, -200C, -300, -400, and -500 series airplanes was published in the Federal Register on September 18, 2003 (68 FR 54684). That action proposed to require replacing the existing screw, nut, and washers that attach the latch cable assembly to the latch block assembly of the door mounted escape slides, with the new, improved screw, nut, and washers. \n\nComments \n\n\tInterested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received. \n\nGenerally Agree With the Proposed AD \n\n\tTwo commenters generally agree with this proposed AD and have no additional comments. \n\nExtend Compliance Time \n\n\tThree commenters request that the proposed compliance time for the replacement be extended from 18 months to 36 months. The commenters state that the extended compliance time would allow for the replacement to be accomplished concurrently with the modification of the escape slide compartment hinge assembly required by AD 2004-02-08, amendment 39-13443 (69 FR 4452, January 30, 2004). In addition, a compliance time of 36 months will allow operators to perform the replacement during the typical overhaul period for escape slides. \n\n\tThe FAA agrees with the commenters' request to extend the compliance time for the replacement. Extending the compliance time by 18 months will not adversely affect safety and will allow the replacement to be performed during regularly scheduled maintenance visits. Paragraph (a) of the AD has been revised to specify a compliance time of 36 months. \n\nClarify Applicability of Parts Installation Paragraph \n\n\tFour commenters request that paragraph (b) of the proposed AD be revised to state specifically that the nut, part number (P/N) BACN10R10L, and screw, P/N NAS623-3-8, cannot be installed in the latch assembly. The commenters state that the intent of the proposed AD is to identify nuts, P/N BACN10R10L, and screws, P/N NAS623-3-8, that are not to be installed on the latch assembly. These parts are used elsewhere throughout the airplane and are not exclusive to the latch assembly. \n\n\tWe agree with the commenters that the intent of the proposed AD is to prevent nuts, P/N BACN10R10L, and screws, P/N NAS623-3-8, from being installed on the latch assembly. We have revised paragraph (b) of the AD to limit the use of nuts, P/N BACN10R10L, and screws, P/N NAS623-3- 8, on the latch block assembly. In addition, we removed the phrase "that was removed from any airplane" to clarify that any nut, P/N BACN10R10L, may not be installed on the latch block assembly of any airplane. \n\nConclusion \n\n\tAfter careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require theadoption of the rule with the changes previously described. The FAA has determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. \n\nCost Impact \n\n\tThere are approximately 2,919 airplanes of the affected design in the worldwide fleet. The FAA estimates that 1,129 airplanes of U.S. registry will be affected by this AD. The FAA estimates that it will take approximately 2 work hours for each airplane specified as Group 1 in the referenced service bulletin, and approximately 1 work hour for each airplane specified as Group 2 in the referenced service bulletin, to accomplish the required actions; the average labor rate is estimated to be $65 per work hour. Parts and materials are standard and are to be supplied by the operator. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $130 per Group 1 airplane, and $65 per Group 2 airplane. \n\n\tThe cost impact figure discussed above is based onassumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions. The manufacturer may cover the cost of replacement parts associated with this AD, subject to warranty conditions. Manufacturer warranty remedies may also be available for labor costs associated with this AD. As a result, the costs attributable to the AD may be less than stated above. \n\nRegulatory Impact \n\n\tThe regulations adopted herein 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. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132. \n\n\tFor the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) 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. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES. \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, pursuant to 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. Section 39.13 is amended by adding the following new airworthiness directive: