[Federal Register: December 31, 2003 (Volume 68, Number 250)]
[Rules and Regulations]
[Page 75394-75396]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr31de03-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-SW-36-AD; Amendment 39-13401; AD 2003-26-04]
RIN 2120-AA64
Airworthiness Directives; Agusta S.p.A. Model A109E Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) for
Agusta S.p.A. (Agusta) Model A109E helicopters. This action requires
certain inspections of the rod-end of the main rotor head damper for
freedom of movement, and depending on the torque required to move the
rod-end, either further inspection for a crack or replacing the rod-
end. This amendment is prompted by reports of rod-end fractures due to
fatigue failure resulting in increased helicopter vibrations. This
condition, if not corrected, could result in failure of the rod-end,
extreme vibrations, and a subsequent forced landing or loss of control
of the helicopter.
DATES: Effective January 15, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 15, 2004.
Comments for inclusion in the Rules Docket must be received on or
before March 1, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 2003-SW-36-AD, 2601 Meacham Blvd., Room
663, Fort Worth, Texas 76137. You may also send comments electronically
to the Rules Docket at the following address: 9-asw-adcomments@faa.gov.
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: The Ente Nazionale per l'Aviazione Civile
(ENAC), the airworthiness authority for Italy, notified the FAA that an
unsafe condition may exist on Agusta Model A109E helicopters. The ENAC
advises that inspections of the rod-end should be carried out as called
for by the manufacturer's service information.
Agusta has issued Bollettino Tecnico (BT) No. 109EP-37, dated July
15, 2003; BT No. 109EP-37, Revision A, dated July 30, 2003; and Errata
Corrige, dated September 2, 2003; which specify an inspection of each
damper rod-end assembly, part number (P/N) Microtecnica 3637GR85, for
seizure or a crack. Agusta reports rod-end fractures due to fatigue
failure originating from the thread under cut of the rod-end resulting
in increased helicopter vibrations. Also, during the first few hours of
operation, the rotational torque of the spherical bearing increases
generating additional loads on the rod-end. ENAC has classified this BT
as mandatory and issued AD Nos. 2003-231, dated July 18, 2003, and
2003-249, dated August 1, 2003, to ensure the continued airworthiness
of these helicopters in Italy.
This helicopter model is manufactured in Italy and is 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 this type design that are certificated for
operation in the United States.
This unsafe condition is likely to exist or develop on other
helicopters of the same type design registered in the United States.
Therefore, this AD is being issued to prevent failure of the rod-end,
extreme vibration, and a subsequent forced landing or loss of control
of the helicopter. This AD requires the following:
[sbull] Within 25 hours time-in-service (TIS), inspect the rod-end
to determine if it can be rotated by hand.
[sbull] If the rod-end can be rotated by hand, no further action is
required.
[sbull] If the rod-end cannot be rotated by hand, determine the
torque value
[[Page 75395]]
required to rotate it by use of a torque wrench.
[sbull] If the torque value is less than 20 Newton-meter (Nm) (177
in-lb) within 25 hours TIS, inspect the rod-end for a crack by a
magnetic particle inspection. If a crack is found, replace the rod-end
assembly with an airworthy part before further flight.
[sbull] If the torque value is 20 Nm or more, replace the rod-end
assembly with an airworthy part before further flight.
The actions must be done using the BT 109EP-37, Revision A, as
amended by the Errata Corrige, described previously. The short
compliance time involved is required because the previously described
critical unsafe condition can adversely affect the controllability of
the helicopter. Therefore, within 25 hours TIS, inspecting the rod-end
to determine if it can be rotated by hand is required. If the rod-end
cannot be rotated by hand, determining the torque value required to
rotate the rod end and, if necessary, replacing the rod-end assembly
with an airworthy part before further flight are required, and this AD
must be issued immediately.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
The FAA estimates that this AD will affect 34 helicopters of U.S.
registry, and the required actions will take approximately 3 work hours
per helicopter to accomplish at an average labor rate of $65 per work
hour. Required parts will cost approximately $450 per helicopter. Based
on these figures, we estimate the total cost of the AD on U.S.
operators to be $21,930 ($645 per helicopter). However, Agusta states
in its BT that it will supply the parts at no cost and will reimburse
up to 2.5 work hours for each terminal at a fixed rate of $40. Assuming
the warranty coverage, the estimated total cost impact on U.S.
operators would be $3,230 ($95 per helicopter).
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available in the Rules Docket for examination by interested persons. A
report that summarizes each FAA-public contact concerned with the
substance of this AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their mailed
comments submitted in response to this rule must submit a self-
addressed, stamped postcard on which the following statement is made:
``Comments to Docket No. 2003-SW-36-AD.'' The postcard will be date
stamped and returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, 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 adding a new airworthiness directive to
read as follows:
2003-26-04 Agusta S.p.A.: Amendment 39-13401. Docket No. 2003-SW-36-
AD.
Applicability: Model A109E helicopters, with a main rotor head
damper, part number (P/N) 109-0111-06-103, with a rod-end assembly,
P/N 3637GR85, with a rod-end, P/N 3637-14, installed, certificated
in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the rod-end, extreme vibrations, and a
subsequent forced landing or loss of control of the helicopter,
accomplish the following:
(a) Within 25 hours time-in-service (TIS), inspect by hand the
rod-end, P/N 3637-14, for freedom of movement around the spherical
bearing, P/N 3637-40.
(1) If the rod-end can be rotated by hand, no further action is
required by this AD.
(2) If the rod-end cannot be rotated by hand, by using a torque
wrench, determine the torque required to rotate the rod-end around
the spherical bearing by following the Compliance Instructions, Part
I, paragraph 3.1, of Agusta Bollettino Tecnico No. 109EP-37,
Revision A, dated July 30, 2003, as amended by the Errata Corrige,
dated September 2, 2003 (BT).
(i) If the torque value is 20 or more Newton-meter (Nm) (177 in-
lb), replace the rod-end assembly with an airworthy rod-end assembly
containing a rod-end, P/N 3637-14, with the letters ``T'', ``R'',
``RT'', ``TR'', or ``TRR'' after the P/N, by following the
Compliance Instructions, paragraphs 3.3.1. through 3.3.3., of the
BT, except you are not required to return the removed rod-end
assembly to Agusta.
(ii) If the torque value is less than 20 Nm, within the next 25
hours TIS, magnetic particle inspect the rod-end for a crack by
following the Compliance Instructions, Part II, of the BT.
(A) If no crack is found, no further action is required by this
AD.
(B) If a crack is found, replace the rod-end assembly with an
airworthy rod-end assembly containing a rod-end, P/N 3637-14 with
the letters ``T'', ``R'', ``RT'', ``TR'', or ``TRR'' after the P/N,
by following the Compliance Instructions, paragraphs 3.3.1. through
3.3.3., of the BT, except you are not required to return the removed
rod-end assembly to Agusta.
[[Page 75396]]
(b) 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 Group, Rotorcraft Directorate, FAA,
for information about previously approved alternative methods of
compliance.
(c) The inspections and replacement of the rod-end assembly must
be done using Agusta Bollettino Tecnico No. 109EP-37, Revision A,
dated July 30, 2003, as amended by the Errata Corrige, dated
September 2, 2003. 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.
(d) This amendment becomes effective on January 15, 2004.
Note: The subject of this AD is addressed in Ente Nazionale per
l'Aviazione Civile (Italy) AD Nos. 2003-231, dated July 18, 2003,
and 2003-249, dated August 1, 2003.
Issued in Fort Worth, Texas, on December 15, 2003.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-31849 Filed 12-30-03; 8:45 am]
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