[Federal Register Volume 69, Number 122 (Friday, June 25, 2004)]
[Rules and Regulations]
[Pages 35511-35512]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-14316]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-15-AD; Amendment 39-13687; AD 2001-24-07 R1]
RIN 2120-AA64


Airworthiness Directives; Agusta S.p.A. Model A109C, A109E, and 
A109K2 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment revises an existing airworthiness directive 
(AD), for the Agusta S.p.A. (Agusta) Model A109C, A109E, and A109K2 
helicopters, that currently requires inspecting the main rotor blade 
(blade) tip cap for bonding separation and a crack, and also requires a 
tap inspection of the tip cap for bonding separation in the blade bond 
area and a dye-penetrant inspection of the tip cap leading edge along 
the welded joint line of the upper and lower tip cap skin shells for a 
crack. This amendment requires those same actions, but corrects a blade 
part number (P/N) that was stated incorrectly in the Applicability 
section of the existing AD. This amendment is prompted by the need to 
correct a blade P/N. The actions specified by this AD are intended to 
prevent failure of a blade tip cap, excessive vibration, and subsequent 
loss of control of the helicopter.

DATES: Effective July 30, 2004.
    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of January 7, 2002.

ADDRESSES: 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html html.

FOR FURTHER INFORMATION CONTACT: Richard Monschke, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort 
Worth, Texas 76193-0110, telephone (817) 222-5116, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 by 
revising AD 2001-24-07, Amendment 39-12523 (66 FR 60144, December 3, 
2001), for the specified Agusta helicopters, was published in the 
Federal Register on January 27, 2004 (69 FR 3859). The action proposed 
to correct a P/N that was stated incorrectly in the previous AD, and to 
require:
     A tap inspection of the upper and lower sides of the tip 
cap for bonding separation and in the tip cap to blade bond area;
     A visual inspection of the upper and lower side of the 
blade tip cap for swelling or deformation; and
     A dye-penetrant inspection of the tip cap leading edge 
along the welded joint line of the upper and lower tip cap skin shells 
for a crack.
    AD 2001-24-07 superseded AD 98-19-04, Amendment 39-11039 (64 FR 
7494, February 16, 1999), Docket No. 98-SW-40-AD. AD 98-19-04 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 2001-24-07 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 dye-penetrant 
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 709-0103-29-109, 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

0
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

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. Section 39.13 is amended by removing Amendment 39-12523 (66 FR 
60144), and by adding a new airworthiness directive (AD), Amendment 39-
13687, to read as follows:

2001-24-07 R1 Agusta S.p.A.: Amendment 39-13687. Docket No. 2001-SW-
15-AD. Revises AD 2001-24-07, Amendment 39-12523.

    Applicability: Model A109C, A109E, and A109K2 helicopters, with 
main rotor blade

[[Page 35512]]

(blade), part number (P/N) 709-0103-01--all 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 time-in-service (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 109-3101-58-1, or a coin (quarter) in the 
area indicated as honeycomb core on Figure 1 of Alert Bollettino 
Tecnico Nos. 109-106, 109K-22, or 109EP-1, 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) Dye-penetrant 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 709-0103-
29-109, 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 dye-penetrant inspection shall be 
done in accordance with Agusta Alert Bollettino Tecnico Nos. 109-
106, 109K-22, or 109EP-1, 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) 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: http://www.archives.gov/federal_register/ code--of--federal-- regulations/
ibr--locations.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. 2000-571, 2000-572, 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. 04-14316 Filed 6-24-04; 8:45 am]
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