FR Doc 04-14316

[Federal Register: June 25, 2004 (Volume 69, Number 122)]
[Rules and Regulations]
[Page 35511-35512]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr25jn04-4]

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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 --

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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