On August 31, 2010, the FAA issued Emergency AD 2010-19-51 for the specified model helicopters, which requires inspecting parts of the servo actuator for certain conditions and replacing any unairworthy parts before further flight. That action was prompted by a collective servo actuator malfunction and a subsequent investigation that revealed the output piston rod assembly (piston rod) had fractured at the threaded end because of stress corrosion cracking. Also, during the investigation of that servo actuator malfunction, a nonconforming grind relief was discovered on a separate piston rod. This condition, if not detected and corrected, could result in failure of the piston rod, failure of the servo actuator, and subsequent loss of control of the helicopter.
Transport Canada, the airworthiness authority for Canada, has issued Canadian AD No. CF-2010-29, dated August 26, 2010 to correct an unsafe condition for the Bell Model 222, 222B, 222U, 230, and 430helicopters. Transport Canada advises that it has been determined that the piston rods of the servo actuators "may be corroded and, consequently, prone for corrosion cracking.'' Also, in one case, "an unapproved repair was found on the piston rod.'' This situation, if not corrected, could result in loss of control of the helicopter.
Bell has issued Alert Service Bulletin (ASB) No. 222-10-109 for the Model 222 and 222B helicopters, ASB No. 222U-10-80 for the Model 222U helicopters, ASB No. 230-10-41 for the Model 230 helicopters, and ASB No. 430-10-44 for the Model 430 helicopters. Each ASB is dated August 18, 2010, and specifies a one-time inspection of all affected servo actuators to verify the condition of the piston rod. Woodward HRT also issued ASB No. 141600-67-02, dated August 18, 2010, attached to each Bell ASB, which specifies inspecting the piston rod for corrosion and nonconforming grind relief. It also contains instructions for reworking and reassembling the unit for operation. Transport Canada classified the ASBs as mandatory and issued AD No. CF-2010-29, dated August 26, 2010, to ensure the continued airworthiness of these helicopters.
This AD differs from the Transport Canada AD in that we require the initial inspection before further flight rather than no later than 5 hours air time upon receiving the AD. Also, this AD requires replacing unairworthy parts with airworthy parts if certain conditions are found and this AD does not add a life limit for the servo actuator rod. Also, this AD does not require a one time rectification and a complete overhaul of the servo actuator after the initial inspection. This AD is an interim action.
These helicopters have been approved by the aviation authority of Canada and are approved for operation in the United States. Pursuant to our bilateral agreement with Canada, they have notified us of the unsafe condition described in the Transport Canada AD. We are issuing this AD because we evaluated all information provided by Transport Canada and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs. Therefore, this AD requires, before further flight:
Disassembling the actuator to gain access to the piston rod.
Cleaning the entire piston rod and nut using Acetone and a nylon bristle brush removing all contaminates to allow for inspection.
Inspecting the grind relief configuration for the piston rod and nut. If the grind relief is unacceptable, replacing the piston rod and the nut with airworthy parts.
Using a 10x or higher magnifying glass, visually inspecting the nut for corrosion or damage to the threads. If you find any corrosion or damage to the threads, replacing the nut with an airworthy nut. Using a 10x or higher magnifying glass, visually inspecting the piston rod for any corrosion, visible lack of cadmium plate (gold or grey color), or damage to the piston rod. If you find any corrosion, visible lack of cadmium plate (gold or grey color), or damage to the piston rod in the "Critical Areas,'' replacing the piston rod with an airworthy piston rod.
If you find any corrosion or visible lack of cadmium plate on the piston rod in areas that are not considered "Critical Areas,'' reworking the piston rod by removing any surface corrosion that has not penetrated into the base material by lightly buffing with scotch-brite. Cleaning the part using Acetone and a nylon bristle brush to remove any residue.
If you find any corrosion that is red or orange in color, magnetic particle inspecting the piston rod for a crack. If you find a crack, replacing the piston rod with an airworthy piston rod.
Inspecting the portion of the piston rod for any bare base metal that is not coated with cadmium plate. If you find any bare base metal on the piston rod in this area, reworking the piston rod by applying brush cadmium plating to all bare and reworked areas.
Reassembling the servo actuator.
After reassembling the servo actuator, marking it with the letter "B'' following the serial number on the name plate using a scribe or vibrating stylus.
Performing a hydraulic system check.
These actions must be accomplished by following specified portions of the ASBs described previously.
The short compliance time involved is required because the previously described critical unsafe condition can adversely affect the structural integrity and controllability of the helicopter. Therefore, inspecting parts of the servo actuator for certain conditions and replacing any unairworthy parts are required before further flight, and this AD must be issued immediately.
Since it was found that immediate corrective action was required, notice and opportunity for prior public comment thereon were impracticable and contrary to the public interest, and good cause existed to make the AD effective immediately by individual letters issued on August 31, 2010 to all known U.S. owners and operators of Bell Helicopter Textron Canada Model 222, 222B, 222U, 230, and 430 helicopters. These conditions still exist, and the AD is hereby published in the Federal Register as an amendment to 14 CFR 39.13 to make it effective to all persons. However, we have made a change to Note 1 of this AD, and we have also clarified that we are not adopting a reduced life limit for the piston rod assembly. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD.
We estimate that this AD will affect 146 helicopters of U.S. registry. There are three servo actuators per helicopter. For a servo actuator that is inspected and does not require rework or repair, removing each servo actuator, performing the inspections, and re- installing it will take approximately four work hours at an average labor rate of $85 per hour. For a servo actuator that is inspected and requires a servo actuator rod to be replaced, removing each servo actuator, performing the inspections, and re-installing an airworthy servo actuator rod will also take approximately four work hours. Each replacement servo actuator rod is estimated to cost $9,000. Based on these figures, we assume that the total cost impact of the AD on U.S. operators will be $289,020, assuming 10% of the fleet (15 helicopters) will need to replace one servo actuator rod per helicopter.
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-2010-1137; Directorate Identifier 2010-SW-079-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:// www.regulations.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).
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 estimated costs to comply with this AD. See the AD docket 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.
2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: