This amendment adopts a new AD for the Schweizer Model 269C, C-1, and D helicopters. This action requires inspecting, modifying, and testing the lateral control trim actuator assembly on certain serial-numbered helicopters. This amendment is prompted by three reported incidents of the inner spring tube separating from the lateral trim control housing resulting in a lateral cyclic control restriction. This condition, if not corrected, could result in the loss of trim control, increased local resistance to right cyclic stick movement, and an emergency landing or subsequent loss of control of the helicopter.
We have reviewed Schweizer Service Bulletins B-283.1 and C1B-017.1, both dated March 4, 2005, and DB-012, dated February 8, 2005, which describe procedures for inspecting, modifying, and testing the lateral control trim actuator assembly, part number (P/N) 269A7316-13.
This unsafe condition is likely to exist or develop on other helicopters of thesame type designs. Therefore, we are issuing this AD to prevent the separation of the inner spring tube from the lateral trim control housing, resulting in the loss of trim control, increased local resistance to right cyclic stick movement, and a subsequent emergency landing or loss of control of the helicopter. This AD requires the following:
For Model 269C, S/N 1865 through 1874, with a prefix of S, and Model 269C-1, S/N 0169 through 0191, before further flight, inspect the lateral control trim actuator assembly for a scuffmark, indentation, or outer spring guide tube deformation. Inspect for security of the inner spring tube in the socket of the lateral trim control housing by rotating and pulling on the inner spring tube. Examine the resin bead around the base of the inner spring tube and housing socket. Resin should be translucent dark pink in color to indicate a good bond.
If a scuffmark, indentation, or deformation exists on the outer spring tube, or the inner spring tube is loose or has motion, or bonding is separated, before further flight, remove the lateral control trim actuator assembly; modify the trim control housing and the inner spring tube; and test run the actuator assembly.
If no scuffmark, indentation, or deformation exists on the outer spring tube, or the inner spring tube is not loose, or the bonding is not separated, within the next 25 hours time-in-service (TIS), modify the lateral control trim actuator assembly.
For Model 269D, Configuration A, S/N 0044 through 0050 with an A suffix, within the next 50 hours TIS, modify the lateral control trim actuator assembly.
Accomplish the actions by following the service bulletins described previously.
The short compliance time involved is required because the previously described critical unsafe condition can adversely affect the controllability of the helicopter. Therefore, inspecting, modifying, and testing the lateral control trim assembly, P/N 269A7316-13, before furtherflight, for Model 269C and C-1 or no later than 50 hours TIS for Model 269D are required, and this AD must be issued immediately.
Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days.
We estimate that this AD will affect 20 helicopters and will take about:
2 work hours to inspect, modify, and test Schweizer Model 269C and C-1 helicopters (for 19 helicopters), and
3 work hours to modify and test Schweizer Model 269D helicopters (for one helicopter).
The average labor rate is $65 per hour.
The cost is about $30 for adhesive, solvent, sandpaper, and nylon or cotton cord.
Based on these figures, we estimate the total cost impact of the AD on U.S. operators to be about $3,606.
Comments Invited
This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include "Docket No. FAA-2005-21217; Directorate Identifier 2005-SW-06-AD" at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov , including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Using the search function of our docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent the comment. You may review the DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477-78), or you may visit http://dms.dot.gov .
Regulatory Findings
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.
For the reasons discussed above, I certify that the regulation:
1. Is not a "significant regulatory action" under Executive Order 12866;
2. Is not a "significant rule" under the 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.
We prepared an economic evaluation of the estimatedcosts to comply with this AD. See the DMS to examine the economic evaluation.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, "General requirements." Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
Accordingly, 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:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: