[Federal Register Volume 66, Number 164 (Thursday, August 23, 2001)]
[Proposed Rules]
[Pages 44320-44322]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-21231]


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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 superseding an existing airworthiness 
directive (AD) for Agusta S.p.A. Model A109C, A109E, and A109K2 
helicopters. That AD requires inspecting between the metal shells and 
honeycomb core by a tapping inspection of the upper and lower sides of 
the main rotor blade (blade) tip cap for bonding separation, by a 
visual inspection for swelling or deformation, and by a visual 
inspection of the welded bead along the leading edge for a crack. This 
action would contain the same requirements as the existing AD but would 
also require 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 proposal 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 
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 on or before October 22, 2001.

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 document 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

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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.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the 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.

Discussion

    On February 5, 1999, the FAA issued AD 98-19-04, Amendment 39-11039 
(64 FR 7494, February 16, 1999), to require inspecting between the 
metal shells and honeycomb core for bonding separation by a tapping 
inspection of the upper and lower sides of the blade tip cap, by a 
visual inspection for swelling or deformation, and by a visual 
inspection of the welded bead along the leading edge of the blade tip 
cap for a crack. That action was prompted by two discoveries of cracks 
in the leading edge of blade tip caps. The cracks were discovered after 
pilots experienced increased vibration during flight. Subsequent 
investigation revealed that bonding separation of the honeycomb 
material in the blade led to deformation and cracking of the blade tip 
cap. The requirements of that AD are intended to prevent a blade tip 
cap failure, excessive vibration, and subsequent loss of control of the 
helicopter.
    Since the issuance of that AD, Agusta S.p.A. has issued Alert 
Bollettino Tecnico (ABT) Nos. 109-106, 109K-22, and 109EP-1, all 
Revision B, and dated December 19, 2000, that specify inspecting the 
tip cap of blades, part number (P/N) 709-0103-01 (all dash numbers) up 
through serial number 1428, preceded by code AJ or EM, for debonds and 
cracks.
    We have identified an unsafe condition that is likely to exist or 
develop on other Agusta S.p.A. Model A109C, A109E, and A109K2 
helicopters of the same type design. The proposed AD would supersede AD 
98-19-04 but would retain the same requirements and would also require 
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 tip cap, P/N 709-0103-29-109, on all affected 
blades would be terminating action for the requirements of this AD.
    We estimate that 44 helicopters of U.S. registry would be affected 
by this proposed AD and that it would 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 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.

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 39-11039 (64 FR 
7494, February 16, 1999), and by adding a new airworthiness directive 
(AD) to read as follows:

Agusta S.p.A. 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 
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 use the authority 
provided in paragraph (f) to request approval from the FAA. This 
approval may address either no action, if the current configuration 
eliminates the unsafe condition, or different actions necessary to 
address the unsafe condition described in this AD. Such a request 
should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any helicopter from the applicability of this AD.

    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

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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.

    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 August 14, 2001.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-21231 Filed 8-22-01; 8:45 am]
BILLING CODE 4910-13-P