AD 20012407 superseded AD 981904, Amendment 3911039 (64 FR 7494, February 16, 1999), Docket No. 98SW40AD. AD 981904 required inspecting between the metal shells and honeycomb core for bonding separation, visually inspecting the blade tip for swelling or deformation, and visually inspecting the welded bead along the leading edge of the blade tip cap for a crack. AD 20012407 retained those requirements, and added a requirement for a tap inspection of the tip cap for bonding separation in the blade bond area, and a dyepenetrant inspection of the tip cap leading edge along the welded joint line of the upper and lower tip cap skin shells for a crack. Installing a tip cap, P/N 709010329109, on an affected blade is a terminating action for the requirements of the existing AD for that blade.

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or the FAA's determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

The FAA estimates that this AD will affect 44 helicopters of U.S. registry, and the actions will take approximately 6 work hours per helicopter to accomplish the initial and repetitive inspection at an average labor rate of $65 per work hour. Based on these figures, we estimate the total cost impact of the AD on U.S. operators to be $17,160, assuming that no blade will need to be replaced as a result of these inspections.

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.

For the reasons discussed above, I certify that this action (1) is not a ``significant regulatory action'' under Executive Order 12866; (2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES.

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 39AIRWORTHINESS 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 removing Amendment 3912523 (66 FR 60144), and by adding a new airworthiness directive (AD), Amendment 39 13687, to read as follows:
20012407 R1 Agusta S.p.A.: Amendment 3913687. Docket No. 2001SW 15AD. Revises AD 20012407, Amendment 3912523.

Applicability: Model A109C, A109E, and A109K2 helicopters, with main rotor blade
[[Page 35512]]
(blade), part number (P/N) 709010301all dash numbers, having a serial number (S/N) up to and including S/N 1428 with a prefix of either ``EM'' or ``A5'' installed, certificated in any category.

Compliance: Required within 10 hours timeinservice (TIS), unless accomplished previously, and thereafter at intervals not to exceed 25 hours TIS.

To prevent failure of a blade tip cap, excessive vibration, and subsequent loss of control of the helicopter, accomplish the following:
(a) Tap inspect the upper and lower sides of each tip cap for bonding separation between the metal shells and the honeycomb core using a steel hammer, P/N 1093101581, or a coin (quarter) in the area indicated as honeycomb core on Figure 1 of Alert Bollettino Tecnico Nos. 109106, 109K22, or 109EP1, all Revision B, and dated December 19, 2000 (ABT), as applicable. Also, tap inspect for bonding separation in the tip cap to blade bond area (no bonding voids are permitted in this area).
(b) Visually inspect the upper and lower sides of each blade tip cap for swelling or deformation.
(c) Dyepenetrant inspect the tip cap leading edge along the welded joint line of the upper and lower tip cap skin shells for a crack in accordance with the Compliance Instructions, paragraph 3, of the applicable ABT.
(d) If any swelling, deformation, crack, or bonding separation that exceeds the prescribed limits in the applicable maintenance manual is found, replace the blade with an airworthy blade. (e) Replacement blades affected by this AD must comply with the repetitive inspection requirements of this AD. Replacing an affected blade with a blade having an airworthy blade tip cap, P/N 7090103 29109, is terminating action for the requirements of this AD for that blade.
(f) 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 Office, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance.
(g) The tap inspection and dyepenetrant inspection shall be done in accordance with Agusta Alert Bollettino Tecnico Nos. 109 106, 109K22, or 109EP1, all Revision B, and all dated December 19, 2000, as applicable. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of January 7, 2002 (66 FR 60144, December 3, 2001). Copies may be obtained from Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605222595. 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 2027416030, or go to: http://www.archives.gov/federal_register/ codeoffederal regulations/
ibrlocations.html.

(h) This amendment becomes effective on July 30, 2004.

Note: The subject of this AD is addressed in Ente Nazionale per l'Aviazionne Civile (Italy) AD Nos. 2000571, 2000572, and 2000 573, all dated December 22, 2000.

Issued in Fort Worth, Texas, on June 16, 2004.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 0414316 Filed 62404; 8:45 am]
BILLING CODE 491013P

FOR FURTHER INFORMATION CONTACT Richard Monschke, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, Texas 761930110, telephone (817) 2225116, fax (817) 2225961.