Airworthiness Directives; Agusta S.p.A. Model A119 Helicopters, 7057-7059 [05-2588]

Download as PDF Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Proposed Rules This previously described unsafe condition is likely to exist or develop on other helicopters of the same type design registered in the United States. Therefore, the proposed AD would require, for Eurocopter Model EC120B helicopters, serial number 1362 and below, a one-time inspection of the halfclamps to determine if they are centered on the friction ring, and if they are not, centering the half-clamps on the friction ring. The actions would have to be accomplished within 50 hours time-inservice (TIS) for helicopters with 500 or more hours TIS; or no later than 550 hours TIS for helicopters with less than 500 hours TIS, in accordance with the alert telex described previously. We estimate that this proposed AD would affect 78 helicopters of U.S. registry. The one-time inspection would take approximately 2 work hours to accomplish, and the modification would take 6 work hours, at an average labor rate of $65 per work hour. Required modification parts would cost approximately $180 per helicopter. Based on these figures, we estimate the total cost impact of the proposed AD on U.S. operators would be $14,700, assuming 8 helicopters would need modification. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. Additionally, this proposed AD would 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 proposed 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 a draft economic evaluation of the estimated costs to comply with this proposed AD. See the DMS to examine the draft 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 VerDate jul<14>2003 16:17 Feb 09, 2005 Jkt 205001 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, Safety. The Proposed Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 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: Eurocopter France: Docket No. FAA–2005– 20289; Directorate Identifier 2003–SW– 55–AD. Applicability: Model EC120B helicopters, serial number 1362 and below, certificated in any category. Compliance: Required within 50 hours time-in-service (TIS) for helicopters with 500 or more hours TIS; or no later than 550 hours TIS for helicopters with less than 500 hours TIS, unless accomplished previously. To detect incorrect positioning of the tail rotor drive shaft (drive shaft) damper halfclamps (half-clamps), and to prevent interference of the half-clamps with the drive shaft, which could result in scoring on the drive shaft, failure of the drive shaft, and subsequent loss of control of the helicopter, accomplish the following: (a) Inspect the half-clamps, part number C651A4103201 or C651A4103202, to determine if they are centered on the friction ring, using the Operational Procedure, paragraph 2.B., of Eurocopter Alert Telex No. 65A004, Revision 1, dated January 27, 2004 (Alert Telex). If the half-clamps are not centered on the friction ring, center the halfclamps on the friction ring in accordance with the Operational Procedure, paragraph 2.B, and Rework Sheet No. EC 120–53–02–04 in Appendix 1 of the Alert Telex. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 7057 (b) 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. (c) Special flight permits will not be issued. Note: The subject of this AD is addressed in Direction Generale De L’Aviation Civile (France) AD No. UF–2003–465, dated December 22, 2003, and AD No. F–2003–465, Revision A, dated January 21, 2004. Issued in Fort Worth, Texas, on February 1, 2005. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05–2586 Filed 2–9–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20291; Directorate Identifier 2004–SW–25–AD] RIN 2120–AA64 Airworthiness Directives; Agusta S.p.A. Model A119 Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: This document proposes adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A119 helicopters. This proposal would require visually inspecting each main transmission support fitting (fitting) attachment bolt (bolt) for a fracture, a crack, or looseness, and verifying the torque on each fitting bolt. This proposal is prompted by two incidents of fatigue failure of the bolts that secure the transmission rear support fittings to the helicopter. The actions specified by this proposed AD are intended to detect a fracture, a crack, or looseness of a fitting bolt, and prevent fatigue failure of a fitting bolt and subsequent loss of control of the helicopter. DATES: Comments must be received on or before April 11, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically; • Government-wide rulemaking Web site: Go to https://www.regulations.gov E:\FR\FM\10FEP1.SGM 10FEP1 7058 Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Proposed Rules and follow the instructions for sending your comments electronically; • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590; • Fax: 202–493–2251; or • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this proposed AD from Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605–222595. You may examine the comments to this proposed AD in the AD docket on the Internet at https://dms.dot.gov. FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5122, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any written data, views, or arguments regarding this proposed AD. Send or deliver your comments to the address listed under the caption ADDRESSES. Include the docket number ‘‘FAA–2005–20291, Directorate Identifier 2004–SW–25–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// 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 proposed rulemaking. 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 or signed 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 https://dms.dot.gov. Examining the Docket You may examine the docket that contains the proposed AD, any comments, and other information in person at the Docket Management VerDate jul<14>2003 16:17 Feb 09, 2005 Jkt 205001 System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800–647– 5227) is located at the plaza level of the Department of Transportation NASSIF Building in Room PL–401 at 400 Seventh Street, SW., Washington, DC. Comments will be available in the AD docket shortly after the DMS receives them. Discussion The Ente Nazionale per l’Aviazione Civile (ENAC), the airworthiness authority for Italy, notified the FAA that an unsafe condition may exist on Agusta Model A119 helicopters. ENAC advises of the need to check the bolts that secure the transmission support fittings to the structure by following the manufacturer’s Bollettino Tecnico 119– 8, dated April 7, 2004. Agusta has issued Bollettino Tecnico No. 119–8, dated April 7, 2004, which specifies a periodic visual inspection to verify the condition (visible damage) of the airframe mounted main transmission fittings attaching hardware, and successively checking the torque of the bolts to exclude the possible presence of looseness and/or a fracture or a crack. ENAC classified this bollettino tecnico as mandatory and issued AD No. 2004–108, dated April 8, 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 us informed of the situation described above. We have 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 previously described unsafe condition is likely to exist or develop on other helicopters of the same type design registered in the United States. Therefore, the proposed AD would require inspecting each fitting bolt, part number (P/N) NAS625–14 and P/N NAS625–18, for a fracture, a crack, or looseness, within 5 hours time-inservice (TIS) and then at intervals not to exceed 10 hours TIS until accomplishing a torque inspection of each fitting bolt, which would have to be accomplished before further flight if looseness is found, or within 25 hours TIS if looseness is not found. If a fracture or a crack is found on any bolt PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 in a fitting, replacing all 4 of the bolts in the fitting would be required. If looseness is detected on any fitting bolt, a torque inspection would be required. If any torque inspection reveals that the torque of any bolt in a fitting is not between 11.3–15.8 Nm (100–140 inchpounds), all 4 of the bolts in the fitting would have to be replaced with airworthy fitting bolts before further flight. The actions would have to be accomplished in accordance with the bolletino tecnico described previously. We estimate that this proposed AD would affect 21 helicopters of U.S. registry. The three inspections (one initial, one repetitive, and the torque inspection) would take approximately 4 work hours to accomplish at an average labor rate of $65 per work hour. (The manufacturer states that it shall recognize a reimbursement of $120 per helicopter for the labor.) Required parts would cost approximately $1,600 per helicopter ($100 per fitting bolt for 16 fitting bolts). Based on these figures, we estimate the total cost impact of the proposed AD on U.S. operators to be $39,060, assuming that no warranty credit is available and that all affected fitting bolts are replaced. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. Additionally, this proposed AD would 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 proposed 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 a draft economic evaluation of the estimated costs to comply with this proposed AD. See the DMS to examine the draft 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 E:\FR\FM\10FEP1.SGM 10FEP1 Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Proposed Rules 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, Safety. The Proposed Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 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: Agusta S.p.A.: Docket No. FAA–2005–20291; Directorate Identifier 2004–SW–25–AD. Applicability: Model A119 helicopters, serial numbers 14001 through 14037, except serial number 14036, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To detect a fracture, a crack, or looseness of a main transmission support fitting (fitting) attachment bolt (bolt) and prevent fatigue failure of a fitting bolt and subsequent loss of control of the helicopter, accomplish the following: (a) Within 5 hours time-in-service (TIS), and then at intervals not to exceed 10 hour TIS until a torque inspection of each fitting bolt is accomplished in accordance with paragraph (b) of this AD, inspect each fitting bolt, part number NAS625–14 and NAS625– 18, for a fracture, a crack, or looseness, using a light and a mirror. (1) On each of the 4 fittings, if a fracture or a crack is found in any bolt, replace all 4 bolts in the fitting with airworthy fitting bolts before further flight. (2) If looseness is found in any bolt in any fitting, inspect each of the 4 bolts on each of the 4 fittings (16 bolts total) to determine if the torque is between 11.3–15.8 Nm (100–140 inch-pounds). If the indicated torque is not VerDate jul<14>2003 16:17 Feb 09, 2005 Jkt 205001 within the acceptable range on any bolt in a fitting, before further flight, remove all 4 bolts in the fitting and replace them with airworthy fitting bolts in accordance with Part II, steps 4.1 through 5., of Agusta Bollettino Tecnico No. 119–8, dated April 7, 2004 (BT). (b) Within 25 hours TIS, inspect each bolt in each fitting to determine if the torque is between 11.3–15.8 Nm (100–140 inchpounds). If the indicated torque is not within the acceptable range on any bolt, before further flight, remove all 4 bolts in the fitting and replace them with airworthy fitting bolts in accordance with Part II, steps 4.1 through 5., of the BT. (c) Accomplishing the inspections specified in paragraphs (a) and (b) constitute terminating actions for the requirements of this AD. (d) 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. (e) Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished, provided that no fracture, crack, or looseness was found during the inspections required by this AD. Note: The subject of this AD is addressed in Ente Nazionale per l’Aviazione Civile (Italy) AD No. 2004–108, dated April 8, 2004. Issued in Fort Worth, Texas, on February 1, 2005. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05–2588 Filed 2–9–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20293; Directorate Identifier 2004–SW–34–AD] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Model AS355E, F, F1, F2, and N Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: This document proposes superseding an existing airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters. That AD currently requires replacing certain main or combiner gearboxes with airworthy gearboxes. PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 7059 Further investigation has shown that the main gearbox is not affected, and this action would require replacing a certain combiner gearbox with a modified airworthy gearbox. This proposal is prompted by a report of a freewheel unit slipping resulting in an engine overspeed and shutdown. Also, this proposal is prompted by the conclusion of the investigation, which finds the freewheel slippage is due to the surface treatment applied to certain freewheel rollers in the combiner gearbox. The actions specified by the proposed AD are intended to prevent an engine overspeed, an engine shutdown, and subsequent loss of control of the helicopter. DATES: Comments must be received by April 11, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically; • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically; • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590; • Fax: 202–493–2251; or • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may examine the comments to this proposed AD in the AD docket on the Internet at https://dms.dot.gov. FOR FURTHER INFORMATION CONTACT: Uday Garadi, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193–0110, telephone (817) 222–5123, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption ADDRESSES. Include the docket number ‘‘FAA–2005–20293, Directorate Identifier 2004–SW–34–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. E:\FR\FM\10FEP1.SGM 10FEP1

Agencies

[Federal Register Volume 70, Number 27 (Thursday, February 10, 2005)]
[Proposed Rules]
[Pages 7057-7059]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-2588]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20291; Directorate Identifier 2004-SW-25-AD]
RIN 2120-AA64


Airworthiness Directives; Agusta S.p.A. Model A119 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for Agusta S.p.A. (Agusta) Model A119 helicopters. This proposal 
would require visually inspecting each main transmission support 
fitting (fitting) attachment bolt (bolt) for a fracture, a crack, or 
looseness, and verifying the torque on each fitting bolt. This proposal 
is prompted by two incidents of fatigue failure of the bolts that 
secure the transmission rear support fittings to the helicopter. The 
actions specified by this proposed AD are intended to detect a 
fracture, a crack, or looseness of a fitting bolt, and prevent fatigue 
failure of a fitting bolt and subsequent loss of control of the 
helicopter.

DATES: Comments must be received on or before April 11, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically;
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov

[[Page 7058]]

and follow the instructions for sending your comments electronically;
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590;
     Fax: 202-493-2251; or
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    You may get the service information identified in this proposed AD 
from Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni 
Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605-222595.
    You may examine the comments to this proposed AD in the AD docket 
on the Internet at https://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, 
Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-
5961.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any written data, views, or arguments 
regarding this proposed AD. Send or deliver your comments to the 
address listed under the caption ADDRESSES. Include the docket number 
``FAA-2005-20291, Directorate Identifier 2004-SW-25-AD'' at the 
beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of the 
proposed AD. We will consider all comments received by the closing date 
and may amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
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 proposed rulemaking. 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 or 
signed 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 https://dms.dot.gov.

Examining the Docket

    You may examine the docket that contains the proposed AD, any 
comments, and other information in person at the Docket Management 
System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone 1-800-
647-5227) is located at the plaza level of the Department of 
Transportation NASSIF Building in Room PL-401 at 400 Seventh Street, 
SW., Washington, DC. Comments will be available in the AD docket 
shortly after the DMS receives them.

Discussion

    The Ente Nazionale per l'Aviazione Civile (ENAC), the airworthiness 
authority for Italy, notified the FAA that an unsafe condition may 
exist on Agusta Model A119 helicopters. ENAC advises of the need to 
check the bolts that secure the transmission support fittings to the 
structure by following the manufacturer's Bollettino Tecnico 119-8, 
dated April 7, 2004.
    Agusta has issued Bollettino Tecnico No. 119-8, dated April 7, 
2004, which specifies a periodic visual inspection to verify the 
condition (visible damage) of the airframe mounted main transmission 
fittings attaching hardware, and successively checking the torque of 
the bolts to exclude the possible presence of looseness and/or a 
fracture or a crack. ENAC classified this bollettino tecnico as 
mandatory and issued AD No. 2004-108, dated April 8, 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 us informed of the 
situation described above. We have 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 previously described unsafe condition is likely to exist or 
develop on other helicopters of the same type design registered in the 
United States. Therefore, the proposed AD would require inspecting each 
fitting bolt, part number (P/N) NAS625-14 and P/N NAS625-18, for a 
fracture, a crack, or looseness, within 5 hours time-in-service (TIS) 
and then at intervals not to exceed 10 hours TIS until accomplishing a 
torque inspection of each fitting bolt, which would have to be 
accomplished before further flight if looseness is found, or within 25 
hours TIS if looseness is not found. If a fracture or a crack is found 
on any bolt in a fitting, replacing all 4 of the bolts in the fitting 
would be required. If looseness is detected on any fitting bolt, a 
torque inspection would be required. If any torque inspection reveals 
that the torque of any bolt in a fitting is not between 11.3-15.8 Nm 
(100-140 inch-pounds), all 4 of the bolts in the fitting would have to 
be replaced with airworthy fitting bolts before further flight. The 
actions would have to be accomplished in accordance with the bolletino 
tecnico described previously.
    We estimate that this proposed AD would affect 21 helicopters of 
U.S. registry. The three inspections (one initial, one repetitive, and 
the torque inspection) would take approximately 4 work hours to 
accomplish at an average labor rate of $65 per work hour. (The 
manufacturer states that it shall recognize a reimbursement of $120 per 
helicopter for the labor.) Required parts would cost approximately 
$1,600 per helicopter ($100 per fitting bolt for 16 fitting bolts). 
Based on these figures, we estimate the total cost impact of the 
proposed AD on U.S. operators to be $39,060, assuming that no warranty 
credit is available and that all affected fitting bolts are replaced.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. Additionally, this proposed 
AD would 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 proposed 
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 a draft economic evaluation of the estimated costs to 
comply with this proposed AD. See the DMS to examine the draft 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

[[Page 7059]]

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, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

Agusta S.p.A.: Docket No. FAA-2005-20291; Directorate Identifier 
2004-SW-25-AD.

    Applicability: Model A119 helicopters, serial numbers 14001 
through 14037, except serial number 14036, certificated in any 
category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect a fracture, a crack, or looseness of a main 
transmission support fitting (fitting) attachment bolt (bolt) and 
prevent fatigue failure of a fitting bolt and subsequent loss of 
control of the helicopter, accomplish the following:
    (a) Within 5 hours time-in-service (TIS), and then at intervals 
not to exceed 10 hour TIS until a torque inspection of each fitting 
bolt is accomplished in accordance with paragraph (b) of this AD, 
inspect each fitting bolt, part number NAS625-14 and NAS625-18, for 
a fracture, a crack, or looseness, using a light and a mirror.
    (1) On each of the 4 fittings, if a fracture or a crack is found 
in any bolt, replace all 4 bolts in the fitting with airworthy 
fitting bolts before further flight.
    (2) If looseness is found in any bolt in any fitting, inspect 
each of the 4 bolts on each of the 4 fittings (16 bolts total) to 
determine if the torque is between 11.3-15.8 Nm (100-140 inch-
pounds). If the indicated torque is not within the acceptable range 
on any bolt in a fitting, before further flight, remove all 4 bolts 
in the fitting and replace them with airworthy fitting bolts in 
accordance with Part II, steps 4.1 through 5., of Agusta Bollettino 
Tecnico No. 119-8, dated April 7, 2004 (BT).
    (b) Within 25 hours TIS, inspect each bolt in each fitting to 
determine if the torque is between 11.3-15.8 Nm (100-140 inch-
pounds). If the indicated torque is not within the acceptable range 
on any bolt, before further flight, remove all 4 bolts in the 
fitting and replace them with airworthy fitting bolts in accordance 
with Part II, steps 4.1 through 5., of the BT.
    (c) Accomplishing the inspections specified in paragraphs (a) 
and (b) constitute terminating actions for the requirements of this 
AD.
    (d) 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.
    (e) Special flight permits may be issued in accordance with 14 
CFR 21.197 and 21.199 to operate the helicopter to a location where 
the requirements of this AD can be accomplished, provided that no 
fracture, crack, or looseness was found during the inspections 
required by this AD.

    Note: The subject of this AD is addressed in Ente Nazionale per 
l'Aviazione Civile (Italy) AD No. 2004-108, dated April 8, 2004.


    Issued in Fort Worth, Texas, on February 1, 2005.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-2588 Filed 2-9-05; 8:45 am]
BILLING CODE 4910-13-P

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