Airworthiness Directives; Agusta S.p.A. Model AB 139 and AW 139 Helicopters, 39572-39574 [E8-14720]

Download as PDF 39572 Federal Register / Vol. 73, No. 133 / Thursday, July 10, 2008 / Rules and Regulations horizontal stabilizer, part number (P/N) 206– 023–119–167, and Model 407 helicopters with horizontal stabilizer, P/N 407–023–801– 109, installed, certificated in any category. mstockstill on PROD1PC66 with RULES Reason (d) The mandatory continuing airworthiness information (MCAI) states: ‘‘Horizontal stabilizers part numbers 206– 023–119–167 and 407–023–801–109 may have manufacturing flaws on the inside surface of the upper and/or lower skin at the tailboom attachment inserts. These flaws may result in cracking of the skin and failure of the horizontal stabilizer.’’ The manufacturer’s service information states that in addition to cracks, the horizontal stabilizer may have deformation or debonding around and between the inserts. This AD requires actions that are intended to address all these unsafe conditions. Actions and Compliance (e) Within the next 100 hours time-inservice (TIS) or 30 days, whichever occurs first, unless done previously. (1) Determine whether you have an affected serial numbered horizontal stabilizer installed by removing the elevators from the horizontal stabilizer. Access the horizontal stabilizer identification tag containing the horizontal stabilizer serial number as shown in Figure 1 and remove the elevators by following the Accomplishment Instructions, Part I, of Bell Helicopter Textron Canada (BHTC) Alert Service Bulletin (ASB) No. 206L–06–141, dated September 12, 2006, applicable to the Model 206L series helicopter (206L ASB) or BHTC ASB No. 407–06–72, dated September 12, 2006, applicable to the Model 407 helicopters (407 ASB). (2) If the serial number on the identification tag is a serial number listed in Table 1 of the 206L ASB or 407 ASB, inspect the horizontal stabilizer as follows: (i) Using a 10× or higher magnifying glass, inspect the horizontal stabilizer for a crack or deformation around the areas of the inserts. Also, using a tap test method, inspect for debonding between the inserts by following the Accomplishment Instructions, Part II, of either the 206L ASB or 407 ASB, as applicable. (ii) If you find a crack, deformation, or debonding, replace the horizontal stabilizer with an airworthy horizontal stabilizer that does not have a serial number listed in Table 1 of the 206L ASB or 407 ASB. Replace the horizontal stabilizer by following the Accomplishment Instructions, Part III, of either the 206L ASB or the 407 ASB, as applicable. (iii) If you do not find a crack, deformation, or debonding, thereafter, at intervals not to exceed 600 hours TIS or during each annual inspection, whichever occurs first, repeat the inspection required by paragraph (e)(2)(i) of this AD. (f) Replacing any horizontal stabilizer containing a serial number listed in Table 1 of 206L ASB or 407 ASB with a horizontal stabilizer that does not contain such a serial number by following the Accomplishment Instructions, Part III, of either the 206L ASB or 407 ASB, as applicable, constitutes VerDate Aug<31>2005 16:54 Jul 09, 2008 Jkt 214001 terminating actions for the requirements of this AD. Differences Between This AD and the MCAI AD (g) The MCAI requires compliance ‘‘within the next 100 hours air time but no later than 9 May 2007.’’ This AD requires compliance within the next 100 hours TIS or 30 days, whichever occurs first, unless done previously. Also, the MCAI requires replacing the horizontal stabilizer by September 30, 2008, and we have not mandated a compliance time for replacing the horizontal stabilizer. Other Information (h) Alternative Methods of Compliance (AMOCs): The Manager, Safety Management Group, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN 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. Related Information (i) MCAI Transport Canada AD No. CF– 2007–03, dated March 27, 2007, contains related information. Air Transport Association of America (ATA) Tracking Code (j) ATA Code 5510: Horizontal Stabilizer Structure. Material Incorporated by Reference (k) You must use the specified portions of Bell Helicopter Textron Canada Alert Service Bulletin No. 206L–06–141 or No. 407–06–72, both dated September 12, 2006, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Bell Helicopter Textron Canada, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437–2862 or (800) 363–8023, fax (450) 433–0272. (3) You may review copies at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Fort Worth, Texas 76193; 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: http://www.archives.gov/federal-register/ cfr/ibr-locations.html. Issued in Fort Worth, Texas on June 19, 2008. Judy I. Carl, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E8–14719 Filed 7–9–08; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0256; Directorate Identifier 2007–SW–01–AD; Amendment 39– 15597; AD 2008–14–02] RIN 2120–AA64 Airworthiness Directives; Agusta S.p.A. Model AB 139 and AW 139 Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. Model AB 139 and AW 139 helicopters. This AD results from mandatory continuing airworthiness information (MCAI) issued by the European Aviation Safety Agency (EASA), the Technical Agent for Italy, with which we have a bilateral agreement, which indicates that the Agusta AB 139’s and AW 139’s Fuselage Frame 5700 middle section is prone to fatigue damage. The actions are intended to detect cracks in the fuselage frame structure and to prevent structural failure in this area. DATES: This AD becomes effective on August 14, 2008. The incorporation by reference of certain publications is approved by the Director of the Federal Register as of August 14, 2008. ADDRESSES: You may examine the AD docket on the Internet at http:// regulations.gov or in person at the Docket Operations office, U.S. Department of Transportation, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., 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 AD from Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605–222595. Examining the AD Docket: The AD docket contains the NPRM, the economic evaluation, any comments received, and other information. The street address and operating hours for the Docket Operations office (telephone (800) 647–5227) are in the ADDRESSES section of this AD. Comments will be available in the AD docket shortly after they are received. FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety Engineer, E:\FR\FM\10JYR1.SGM 10JYR1 Federal Register / Vol. 73, No. 133 / Thursday, July 10, 2008 / Rules and Regulations FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5122, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to Agusta S.p.A. Model AB 139 and AW 139 helicopters. That NPRM was published in the Federal Register on March 7, 2008 (73 FR 12299). That NPRM proposed to require repetitive inspections of the fuselage frame structure for a crack, and if a crack is found, repairing the crack before further flight in accordance with an FAAapproved procedure. You may obtain further information by examining the MCAI and any related service information in the AD docket. Comments By publishing the NPRM, we gave the public an opportunity to participate in developing this AD. However, we received no comment on the NPRM or on our determination of the cost to the public. Therefore, based on our review and evaluation of the available data, we have determined that air safety and the public interest require adopting the AD as proposed except for some formatting changes. These changes will neither increase the economic burden on any operator nor increase the scope of this AD. Relevant Service Information Agusta S.p.A. has issued Bollettino Tecnico No. 139–018, Revision B, dated October 18, 2006. The actions described in the MCAI are intended to correct the same unsafe condition as that identified in the service information. mstockstill on PROD1PC66 with RULES Differences Between This AD and the MCAI AD This AD differs from the MCAI in that the MCAI states ‘‘When damage or cracks are found, before next flight, contact the TC Holder for further instructions.’’ This AD requires repairing the crack before further flight in accordance with an FAA-approved procedure if a crack is found. Also, this AD requires that the inspection be performed based on ‘‘hours time-inservice’’ rather than ‘‘flight hours,’’ as stated in the MCAI. Costs of Compliance We estimate that this AD will affect about 17 helicopters of U.S. registry. We also estimate that it will take about 1 work-hour per helicopter to comply with the initial and each subsequent VerDate Aug<31>2005 16:54 Jul 09, 2008 Jkt 214001 recurring inspection required by this AD. The average labor rate is $80 per work-hour. Assuming that 3 recurring inspections will be performed on each of the affected helicopters every year after the initial inspection, and that 2 of the affected helicopters will require repairs to the fuselage middle frame section at $10,000 per repair during the service life of these helicopters, we estimate the cost of this AD as follows: • Initial Inspection Costs: 1 × 80 × 17 = $1360. • Subsequent Recurring Inspection Costs over the next 20 years: 1 × 3 × 20 × 80 × 17 = $81,600. • Repair Costs: 2 × 10,000 = $20,000. Based on these figures, we estimate the cost of this AD on U.S. operators to be $102,960, or $6,056 per helicopter. We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. 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 helicopters identified in this rulemaking action. Regulatory Findings We 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. Therefore, I certify this AD: 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. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 39573 § 39.13 [Amended] 2. The FAA amends 39.13 by adding the following new AD: I 2008–14–02 Agusta S.p.A.: Amendment 39– 15597. Docket No. FAA–2008–0256; Directorate Identifier 2007–SW–01–AD. Effective Date (a) This airworthiness directive (AD) becomes effective on August 14, 2008. Other Affected ADs (b) None. Applicability (c) This AD applies to Agusta S.p.A. Model AB 139 and AW 139 helicopters, certificated in any category. Reason (d) This AD results from mandatory continuing airworthiness information (MCAI) issued by the European Aviation Safety Agency (EASA), the Technical Agent for Italy, with which we have a bilateral agreement, which indicates that the Agusta AB/AW 139’s Fuselage Frame 5700 middle section is prone to fatigue damage. These fatigue cracks constitute an unsafe condition. The actions are intended to detect cracks in the fuselage frame structure and to prevent structural failure in this area. Actions and Compliance (e) Required as indicated, unless already done. (1) Within the next 10 hours time-inservice (TIS), or upon accumulating 100 hours TIS since new, whichever occurs later, inspect the fuselage frame 5700 middle section in accordance with the Compliance Instructions, pargraphs 1. through 4., of Agusta Bollettino Tecnico No. 139–018, Revision B, dated October 18, 2006; (2) Thereafter, at intervals not exceeding 100 hours TIS, repeat the inspection as required by paragraph (e)(1) of this AD. (3) If a crack is found, before further flight, repair the crack in accordance with an FAAapproved procedure. E:\FR\FM\10JYR1.SGM 10JYR1 39574 Federal Register / Vol. 73, No. 133 / Thursday, July 10, 2008 / Rules and Regulations Differences Between This AD and the MCAI AD DEPARTMENT OF TRANSPORTATION (f) This AD differs from the MCAI as follows: (1) The MCAI states ‘‘When damage or cracks are found, before next flight, contact the TC Holder for further instructions.’’ If a crack is found, this AD requires repairing the crack before further flight in accordance with an FAA-approved procedure. (2) This AD requires that the inspection be performed based on ‘‘hours time-in-service’’ not ‘‘flight hours.’’ Federal Aviation Administration Other Information (g) Alternative Methods of Compliance (AMOCs): The Manager, Safety Management Group, FAA, FAA, ATTN: 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, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (h) European Aviation Safety Agency (EASA) Airworthiness Directive No. 2006– 0357, dated November 29, 2006, contains related information. Air Transport Association of America (ATA) Tracking Code (i) ATA Code 5700: Fuselage frame middle section. Material Incorporated by Reference mstockstill on PROD1PC66 with RULES (j) You must use the specified portions of Agusta Bollettino Tecnico No. 139–018, Revision B, dated October 18, 2006, to do the actions required. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605–222595. (3) You may review copies at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Fort Worth, Texas 76193; 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: http://www.archives.gov/federal-register/ cfr/ibr-locations.html. Issued in Fort Worth, Texas on June 19, 2008. Judy Carl, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E8–14720 Filed 7–9–08; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 16:54 Jul 09, 2008 Jkt 214001 14 CFR Part 39 [Docket No. FAA–2007–0218; Directorate Identifier 92–ANE–56–AD; Amendment 39– 15602; AD 2008–14–07] RIN 2120–AA64 Airworthiness Directives; Lycoming Engines, Fuel Injected Reciprocating Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for certain fuel injected reciprocating engines manufactured by Lycoming Engines. That AD currently requires inspection, and replacement if necessary, of externally mounted fuel injector fuel lines. This AD requires the same actions but adds additional engine models and clarifies certain compliance time wording. This AD also exempts engines that have a Maintenance and Overhaul Manual with an Airworthiness Limitations Section that requires inspection and replacement, if necessary, of externally mounted fuel injector lines. This AD results from Lycoming Engines revising their Mandatory Service Bulletin to add new engine models requiring inspection, and from the need to clarify a repetitive inspection compliance time. We are issuing this AD to prevent failure of the fuel injector fuel lines that would allow fuel to spray into the engine compartment, resulting in an engine fire. DATES: This AD becomes effective August 14, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of August 14, 2008. ADDRESSES: You can get the service information identified in this AD from Lycoming Engines, 652 Oliver Street, Williamsport, PA 17701, or go to http://www.lycoming.textron.com. The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: Norm Perenson, Aerospace Engineer, New York Aircraft Certification Office, FAA, Engine & Propeller Directorate, 1600 Stewart Avenue, Suite 410, PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Westbury, NY 11590; e-mail: Norman.perenson@faa.gov; telephone (516) 228–7337; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by superseding AD 2002–26–01, Amendment 39–12986 (67 FR 78965, December 27, 2002), with a proposed AD. The proposed AD applies to certain fuel injected reciprocating engines manufactured by Lycoming Engines. We published the proposed AD in the Federal Register on January 2, 2008 (73 FR 87). That action proposed to: • Require the same actions as AD 2002–26–01; and • Add additional engine models, clarify certain compliance time wording; and • Exempt engines that have a Maintenance and Overhaul Manual with an Airworthiness Limitations Section that requires inspection and replacement, if necessary, of externally mounted fuel injector lines. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. One commenter, a private citizen, states that in the proposed AD, we wish to exempt engines that have a maintenance manual that deals with this subject. He asks how the mechanic is to know if an engine has a maintenance manual, if the mechanic does not have access to that manual, unless we list the specific engines that are not applicable to the proposed AD. He states that we should either make the AD applicable to fuel injected Lycoming Engines and then list the applicable and nonapplicable engines, or do not change the AD. We do not agree. If the engine has an ‘‘I’’ in the prefix of the engine model and the engine has external fuel lines, the fuel lines require inspection. For engines that have a Maintenance Manual, the required inspection will be described in the Airworthiness E:\FR\FM\10JYR1.SGM 10JYR1

Agencies

[Federal Register Volume 73, Number 133 (Thursday, July 10, 2008)]
[Rules and Regulations]
[Pages 39572-39574]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-14720]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0256; Directorate Identifier 2007-SW-01-AD; 
Amendment 39-15597; AD 2008-14-02]
RIN 2120-AA64


Airworthiness Directives; Agusta S.p.A. Model AB 139 and AW 139 
Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for Agusta 
S.p.A. Model AB 139 and AW 139 helicopters. This AD results from 
mandatory continuing airworthiness information (MCAI) issued by the 
European Aviation Safety Agency (EASA), the Technical Agent for Italy, 
with which we have a bilateral agreement, which indicates that the 
Agusta AB 139's and AW 139's Fuselage Frame 5700 middle section is 
prone to fatigue damage. The actions are intended to detect cracks in 
the fuselage frame structure and to prevent structural failure in this 
area.

DATES: This AD becomes effective on August 14, 2008.
    The incorporation by reference of certain publications is approved 
by the Director of the Federal Register as of August 14, 2008.

ADDRESSES: You may examine the AD docket on the Internet at http://
regulations.gov or in person at the Docket Operations office, U.S. 
Department of Transportation, M-30, West Building Ground Floor, Room 
W12-140, 1200 New Jersey Avenue, SE., 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 AD from 
Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni Agusta 
520, telephone 39 (0331) 229111, fax 39 (0331) 229605-222595.
    Examining the AD Docket: The AD docket contains the NPRM, the 
economic evaluation, any comments received, and other information. The 
street address and operating hours for the Docket Operations office 
(telephone (800) 647-5227) are in the ADDRESSES section of this AD. 
Comments will be available in the AD docket shortly after they are 
received.

FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety 
Engineer,

[[Page 39573]]

FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort 
Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to Agusta S.p.A. Model AB 139 
and AW 139 helicopters. That NPRM was published in the Federal Register 
on March 7, 2008 (73 FR 12299). That NPRM proposed to require 
repetitive inspections of the fuselage frame structure for a crack, and 
if a crack is found, repairing the crack before further flight in 
accordance with an FAA-approved procedure. You may obtain further 
information by examining the MCAI and any related service information 
in the AD docket.

Comments

    By publishing the NPRM, we gave the public an opportunity to 
participate in developing this AD. However, we received no comment on 
the NPRM or on our determination of the cost to the public. Therefore, 
based on our review and evaluation of the available data, we have 
determined that air safety and the public interest require adopting the 
AD as proposed except for some formatting changes. These changes will 
neither increase the economic burden on any operator nor increase the 
scope of this AD.

Relevant Service Information

    Agusta S.p.A. has issued Bollettino Tecnico No. 139-018, Revision 
B, dated October 18, 2006. The actions described in the MCAI are 
intended to correct the same unsafe condition as that identified in the 
service information.

Differences Between This AD and the MCAI AD

    This AD differs from the MCAI in that the MCAI states ``When damage 
or cracks are found, before next flight, contact the TC Holder for 
further instructions.'' This AD requires repairing the crack before 
further flight in accordance with an FAA-approved procedure if a crack 
is found. Also, this AD requires that the inspection be performed based 
on ``hours time-in-service'' rather than ``flight hours,'' as stated in 
the MCAI.

Costs of Compliance

    We estimate that this AD will affect about 17 helicopters of U.S. 
registry. We also estimate that it will take about 1 work-hour per 
helicopter to comply with the initial and each subsequent recurring 
inspection required by this AD. The average labor rate is $80 per work-
hour. Assuming that 3 recurring inspections will be performed on each 
of the affected helicopters every year after the initial inspection, 
and that 2 of the affected helicopters will require repairs to the 
fuselage middle frame section at $10,000 per repair during the service 
life of these helicopters, we estimate the cost of this AD as follows:
     Initial Inspection Costs: 1 x 80 x 17 = $1360.
     Subsequent Recurring Inspection Costs over the next 20 
years: 1 x 3 x 20 x 80 x 17 = $81,600.
     Repair Costs: 2 x 10,000 = $20,000.
    Based on these figures, we estimate the cost of this AD on U.S. 
operators to be $102,960, or $6,056 per helicopter.

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 helicopters identified in this 
rulemaking action.

Regulatory Findings

    We 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.
    Therefore, I certify this AD:
    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 and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends 39.13 by adding the following new AD:

2008-14-02 Agusta S.p.A.: Amendment 39-15597. Docket No. FAA-2008-
0256; Directorate Identifier 2007-SW-01-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective on 
August 14, 2008.

Other Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Agusta S.p.A. Model AB 139 and AW 139 
helicopters, certificated in any category.

Reason

    (d) This AD results from mandatory continuing airworthiness 
information (MCAI) issued by the European Aviation Safety Agency 
(EASA), the Technical Agent for Italy, with which we have a 
bilateral agreement, which indicates that the Agusta AB/AW 139's 
Fuselage Frame 5700 middle section is prone to fatigue damage. These 
fatigue cracks constitute an unsafe condition. The actions are 
intended to detect cracks in the fuselage frame structure and to 
prevent structural failure in this area.

Actions and Compliance

    (e) Required as indicated, unless already done.
    (1) Within the next 10 hours time-in-service (TIS), or upon 
accumulating 100 hours TIS since new, whichever occurs later, 
inspect the fuselage frame 5700 middle section in accordance with 
the Compliance Instructions, pargraphs 1. through 4., of Agusta 
Bollettino Tecnico No. 139-018, Revision B, dated October 18, 2006;
    (2) Thereafter, at intervals not exceeding 100 hours TIS, repeat 
the inspection as required by paragraph (e)(1) of this AD.
    (3) If a crack is found, before further flight, repair the crack 
in accordance with an FAA-approved procedure.

[[Page 39574]]

Differences Between This AD and the MCAI AD

    (f) This AD differs from the MCAI as follows:
    (1) The MCAI states ``When damage or cracks are found, before 
next flight, contact the TC Holder for further instructions.'' If a 
crack is found, this AD requires repairing the crack before further 
flight in accordance with an FAA-approved procedure.
    (2) This AD requires that the inspection be performed based on 
``hours time-in-service'' not ``flight hours.''

Other Information

    (g) Alternative Methods of Compliance (AMOCs): The Manager, 
Safety Management Group, FAA, FAA, ATTN: 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, has the authority to approve AMOCs for 
this AD, if requested using the procedures found in 14 CFR 39.19.

Related Information

    (h) European Aviation Safety Agency (EASA) Airworthiness 
Directive No. 2006-0357, dated November 29, 2006, contains related 
information.

Air Transport Association of America (ATA) Tracking Code

    (i) ATA Code 5700: Fuselage frame middle section.

Material Incorporated by Reference

    (j) You must use the specified portions of Agusta Bollettino 
Tecnico No. 139-018, Revision B, dated October 18, 2006, to do the 
actions required.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni 
Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605-222595.
    (3) You may review copies at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Fort Worth, Texas 
76193; 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: http://www.archives.gov/
federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas on June 19, 2008.
Judy Carl,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-14720 Filed 7-9-08; 8:45 am]
BILLING CODE 4910-13-P