Daily Rules, Proposed Rules, and Notices of the Federal Government
Comments for inclusion in the Rules Docket must be received on or before October 1, 2004.
The service information referenced in this AD may be obtained from Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605-222595. This information may be examined at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to:
This amendment adopts a new AD for Agusta Model A109K2 helicopters. This action requires dye-penetrant inspecting the trunnion assembly for a crack at specified intervals, replacing any cracked trunnion with an airworthy trunnion, and reporting any cracked trunnion. This amendment is prompted by the report of an accident involving a tail rotor hub and blade assembly separating from the helicopter due to fatigue failure of the trunnion. This condition, if not detected, could result in failure of the trunnion, loss of the tail rotor hub and blade assembly, and subsequent loss of control of the helicopter.
Ente Nazionale per l'Aviazione Civile (ENAC), the airworthiness authority for Italy, notified the FAA that an unsafe condition may exist on Agusta Model A109K2 helicopters with trunnion assembly, part number (P/N) 109-0131-05 (all dashes), installed. ENAC advises of the need to carry out checks and inspections of the cracked trunnion assembly as specified in the manufacturer's technical bulletin.
Agusta issued Alert Bollettino Tecnico No. 109K-37, dated February 13, 2004 (ABT). The ABT specifies inspecting the trunnion assembly, P/N 109-0131-05 (all dashes), for a crack within either 10 or 150 operating hours depending on the accumulated operating hours and subsequently every 150 operating hours. ENAC classified this ABT as mandatory and issued AD No 2004-068, dated February 18, 2004, to ensure the continued airworthiness of these helicopters in Italy.
This helicopter model is manufactured in Italy and is type certificated for operation in the United States under the provisions of 14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the applicable bilateral agreement, ENAC has kept the FAA informed of the situation described above. The FAA has examined the findings of ENAC, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States.
This unsafe condition is likely to exist or develop on other helicopters of the same type design registered in the United States. Therefore, this AD is being issued to prevent failure of the trunnion and subsequent loss of control of the helicopter. This AD requires:
• Dye-penetrant inspecting the trunnion, P/N 109-0131-05 (all dash numbers):
• With 150 or more hours time-in-service (TIS), within the next 10 hours TIS; and
• With less than 150 hours TIS, at 150 hours TIS; and
• Thereafter, at intervals not to exceed 150 hours TIS.
• Replacing any cracked trunnion with an airworthy trunnion before further flight.
• Reporting information about any cracked trunnion to Richard Monschke, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, Texas 76193-0110, telephone (817) 222-5116, fax (817) 222-5961.
The cause for the crack in the trunnion has not been determined and is still under investigation. Therefore, the initial dye-penetrant inspection of the trunnion for a crack is required within the next 10 hours TIS, a very short compliance time interval. Additionally, based on the TIS utilization rate of these model helicopters, the 150-hour constitutes a very short compliance time. Therefore, the initial and repetitive inspections are deemed necessary as an emergency action to control the hazard until the cause of the cracks are identified because the previously described critical unsafe condition can adversely affect the controllability and structural integrity of the helicopter. Hence, 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.
The FAA estimates that this AD will:
• Affect 4 helicopters;
• Take about 8 work hours at an average labor rate of $65 per work hour for 4 inspections yearly;
• Cost about $200 for consumable materials per helicopter; and
• Cost about $2320 for a trunnion assembly and $23 for a lock washer, assuming a one-time replacement. However, the manufacturer states in the ABT that it will replace one trunnion if the trunnion is scrapped.
Based on these figures, the total estimated cost impact of the AD on U.S. operators will be $18,492 or 9,212, assuming the manufacturer replaces the trunnion free as stated in the ABT.
Although this action is in the form of a final rule that involves requirements affecting flight safety and, thus, was not preceded by notice and an opportunity for public comment, comments are invited on this rule. Interested persons are invited to comment on this rule by submitting such written data, views, or arguments as they may desire. Communications should identify the Rules Docket number and be submitted in triplicate to the address specified under the caption
Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the rule. All comments submitted will be available in the Rules Docket for examination by interested persons. A report that summarizes each FAA-public contact concerned with the substance of this AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their mailed comments submitted in response to this rule must submit a self-addressed, stamped postcard on which the following statement is made: “Comments to Docket No. 2004-SW-14-AD. The postcard will be date stamped and returned to the commenter.
The 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.
The FAA has determined that this regulation is an emergency regulation that must be issued immediately to correct an unsafe condition in aircraft, and that it is not a “significant regulatory action” under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules Docket. A copy of it, if filed, may be obtained from the Rules Docket at the location provided under the caption
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
49 U.S.C. 106(g), 40113, 44701.
To detect a crack and prevent fatigue failure of the trunnion, loss of the tail rotor hub and blade assembly, and subsequent loss of control of the helicopter, do the following:
(a) Using a qualified Level II Inspector and following the Compliance Instructions, paragraphs 1. through 8., of Agusta Bollettino Tecnico No. 109K-37, dated February 13, 2004, dye penetrant inspect the trunnion for a crack as follows:
(1) Unless accomplished previously, within 10 hours time-in-service (TIS) for trunnions with 150 or more hours TIS;
(2) Unless accomplished previously, on or before accumulating 150 hours TIS for trunnions with less than 150 hours TIS; and
(3) Thereafter, at intervals not to exceed 150 hours TIS.
(b) If a crack is found, before further flight, replace the cracked trunnion with an airworthy trunnion before further flight.
(1) Within 5 days, report the part number, serial number, total hours TIS, and a description of the crack to Richard Monschke, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, Texas 76193-0110, telephone (817) 222-5116, fax (817) 222-5961.
(2) Information collection requirements contained in this AD have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501
(c) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance.
(d) Do the inspection following Agusta Bollettino Tecnico No. 109K-37, dated February 13, 2004. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605-222595. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to:
(e) This amendment becomes effective on August 17, 2004.
The subject of this AD is addressed in Ente Nazionale per l'Aviazione Civile (Italy) AD No. 2004-068, dated February 18, 2004.