[Federal Register Volume 69, Number 17 (Tuesday, January 27, 2004)]
[Proposed Rules]
[Pages 3859-3861]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-1687]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-15-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to revise an existing airworthiness 
directive (AD) for Agusta S.p.A. (Agusta) Model A109C, A109E, and 
A109K2 helicopters. That AD 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

[[Page 3860]]

of the upper and lower tip cap skin shells for a crack. This action 
would require those same actions, but would correct a blade part number 
(P/N) that was stated incorrectly in the Applicability section of the 
existing AD. This proposal is prompted by the need to correct a blade 
P/N. The actions specified by the proposed AD are intended to prevent 
failure of a blade tip cap, excessive vibration, and subsequent loss of 
control of the helicopter.

DATES: Comments must be received by March 29, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2001-SW-15-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: [email protected]. 
Comments may be inspected at the Office of the Regional Counsel between 
9 a.m. and 3 p.m., Monday through Friday, except Federal holidays.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications should identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their mailed 
comments submitted in response to this proposal must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2001-SW-15-AD.'' The postcard will be date 
stamped and returned to the commenter.

Discussion

    On December 19, 2000, Agusta issued Alert Bollettino Tecnico Nos. 
109-106, 109K-22, and 109EP-1, all Revision B, which specified 
inspecting for debond and cracks at the tip cap of blades, P/N 709-
0103-01, all dash numbers, through serial numbers 1428 with a prefix of 
``A5'' or ``EM''.
    The Ente Nazionale per l'Aviazionne Civile (ENAC), the 
airworthiness authority for Italy, classified these technical bulletins 
as mandatory and issued AD Nos. 2000-571, 2000-572, and 2000-573, all 
dated December 22, 2000, requiring an inspection of the tip cap of 
blades for disbonds or cracks on the specified Agusta Model A109C, 
A109E, and A109K2 helicopters.
    These helicopter models are manufactured in Italy and are type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral agreement, ENAC has kept the FAA informed of the 
situation described above. The FAA has examined the findings of ENAC, 
reviewed all available information, and determined that AD action is 
necessary for products of these type designs that are certificated for 
operation in the United States.
    On November 21, 2001, the FAA issued AD 2001-24-07, Amendment 39-
12523 (66 FR 60144, December 3, 2001), which superseded AD 98-19-04, 
Amendment 39-11039, 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. That action was 
prompted by three occurrences in which the blade tip cap leading edge 
opened in flight due to cracks, resulting in excessive helicopter 
vibration. That condition, if not corrected, could result in failure of 
a blade tip cap, excessive vibration, and subsequent loss of control of 
the helicopter.
    Since issuing AD 2001-24-07, we discovered that a blade P/N was 
incorrectly stated in the Applicability section of the AD. P/N 709-
0130-01-all dash numbers should have been stated as P/N 709-0103-01-all 
dash numbers.
    The previously described unsafe condition is likely to exist or 
develop on other helicopters of these same type designs. Therefore, the 
proposed AD would revise AD 2001-24-07 to correct the P/N and to 
continue 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.
    The FAA estimates that this proposed AD would affect 44 helicopters 
of U.S. registry, and the proposed actions would 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 proposed 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 proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (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) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

[[Page 3861]]

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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.


Sec. 39.13  [Amended]

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

Agusta S.p.A.: 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 (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.

    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 January 16, 2004.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-1687 Filed 1-26-04; 8:45 am]
BILLING CODE 4910-13-P