AD 2001-24-07

[Federal Register Volume 66, Number 232 (Monday, December 3, 2001)]
[Rules and Regulations]
[Pages 60144-60145]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-29591]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-15-AD; Amendment 39-12523; AD 2001-24-07]
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 supersedes an existing airworthiness directive 
(AD) that applies to Agusta S.p.A. (Agusta) Model A109C, A109E, and 
A109K2 helicopters and currently requires inspecting the main rotor 
blade (blade) tip cap for bonding separation and a crack. This 
amendment contains the same requirements as the existing AD but 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 is prompted by three occurrences in 
which the blade tip cap leading edge opened in flight due to cracks, 
resulting in excessive helicopter vibration. 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 January 7, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved 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 Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

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 
superseding AD 98-19-04, Amendment 39-11039 (64 FR 7494, February 16, 
1999), which applies to Agusta Model A109C, A109E, and A109K2 
helicopters, was published in the Federal Register on August 23, 2001 
(66 FR 44320). That action proposed to supersede AD 98-19-04, which 
requires 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. This AD retains the requirements 
of AD 98-19-04 and also requires 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 tip 
caps, P/N 709-0103-29-109, on all affected blades is terminating action 
for the requirements of this AD.
    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 except for updating the language in 
Note 1 and adding ``Agusta'' before ``Alert Bollettino Tecnico'' in 
paragraph (a). These changes will neither increase the economic burden 
on any operator nor increase the scope of the AD.
    The FAA estimates that 44 helicopters of U.S. registry will be 
affected by this AD and that it will take approximately 6 work hours 
per helicopter for the initial and repetitive inspections of the fleet. 
The average labor rate is $60 per work hour. Based on these figures, 
the total cost impact of the proposed AD on U.S. operators is estimated 
to be $15,840. This estimate is based on the assumption 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 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

[[Page 60145]]

Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing Amendment 39-11039 (64 FR 
7494, February 16, 1999), and by adding a new airworthiness directive 
(AD), Amendment 39-12523, to read as follows:

2001-24-07  Agusta S.p.A.: Amendment 39-12523. Docket No. 2001-SW-
15-AD. Supersedes AD 98-19-04, Amendment 39-11039, Docket No. 98-SW-
40-AD.

    Applicability: Model A109C, A109E, and A109K2 helicopters, with 
main rotor blade (blade), part number (P/N) 709-0130-01--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.

    Note 1: This AD applies to each helicopter identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise modified, altered, or repaired in the area subject to the 
requirements of this AD. For helicopters that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (f) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    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 Agusta 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) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Regulations Group, Rotorcraft 
Directorate, FAA. Operators shall submit their requests through an 
FAA Principal Maintenance Inspector, who may concur or comment and 
then send it to the Manager, Regulations Group.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (g) A special flight permit may be issued under 14 CFR 21.197 
and 21.199 to operate the helicopter to a location where the 
requirements of this AD can be accomplished. No special flight 
permit will be issued for any flight with a known tip cap crack.
    (h) The inspections shall be done in accordance with Figure 1 
and paragraph 3 of Agusta Alert Bollettino Tecnico Nos. 109-106, 
109K-22, or 109EP-1, all Revision B, and dated December 19, 2000. 
This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. 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 Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
    (i) This amendment becomes effective on January 7, 2002.

    Note 3: The subject of this AD is addressed in Ente Nazionale 
per l'Aviazionne Civile (Italy) AD's 2000-571, 2000-572, and 2000-
573, all dated December 22, 2000.


    Issued in Fort Worth, Texas, on November 21, 2001.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-29591 Filed 11-30-01; 8:45 am]
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