This amendment adopts a new AD for the MDHI Model 500N and 600N helicopters. This action requires using a bright light and a 10x or higher magnifying glass to inspect each connector for corrosion pitting or cracking. If corrosion pitting or cracking is found, this AD also requires replacing the cable assembly with an airworthy cable assembly before further flight. This amendment is prompted by a report of a failure of a cable assembly due to a stress corrosion crack. The actions specified in this AD are intended to detect a corrosion-pitted or cracked connector and to prevent failure of a cable assembly and subsequent loss of control of the helicopter.
We have reviewed MDHI Service Bulletin SB500N-027, SB600N-042, dated May 3, 2004 (SB). The SB describes procedures for inspecting the connectors on the forward and center cable assemblies for corrosion pitting or cracking. Also, the SB specifies replacing the cable assembly if corrosion pitting or crackingis found on the connectors.
This unsafe condition is likely to exist or develop on other helicopters of the same type design. Therefore, this AD is being issued to detect a corrosion-pitted or cracked connector on a cable assembly and to prevent failure of the cable assembly, and subsequent loss of control of the helicopter. This AD requires a one-time inspection of the connectors on the cable assemblies for corrosion pitting or cracking. If corrosion pitting or cracking is found, this AD also requires replacing the cable assembly with an airworthy cable assembly before further flight. Accomplish the actions by following the SB described previously.
The short compliance time involved is required because the previously described critical unsafe condition can adversely affect the controllability or structural integrity of the helicopter. Therefore, within the next 10 hours time-in-service or 30 days, whichever comes first, using a bright light and a 10X or higher magnifying glass, inspect each connector for corrosion pitting or cracking. If corrosion pitting or cracking is found, replacing the cable assembly with an airworthy cable assembly is required before further flight and this AD must be issued immediately. Inspecting each connector and replacing the cable assembly if corrosion pitting or cracking is found is terminating action for the requirements of this AD.
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 66 helicopters. The inspections will take about 1 work hour at an average labor rate of $65 per work hour. Required parts will cost about $4520 per helicopter. Based on these figures, we estimate the total cost impact of the AD on U.S. operators to be $4,290 assuming no parts will need to be replaced.
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-2004-19223; Directorate Identifier 2004-SW-20-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 .
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 estimated costs to comply with this AD. See the DMS to examine the economic evaluation.
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.
39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: