[Federal Register Volume 64, Number 243 (Monday, December 20, 1999)]
[Rules and Regulations]
[Pages 71009-71010]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-32580]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-SW-64-AD; Amendment 39-11472; AD 99-26-13]
RIN 2120-AA64
Airworthiness Directives; Agusta S.p.A. Model A109A and A109A II
Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to Agusta Model A109A and A109A II helicopters, that
currently requires inspecting each tail rotor blade (blade) for a crack
and replacing any cracked blade. This amendment requires, before
further flight, inspecting any blade with 400 or more hours time-in-
service (TIS) for a crack and replacing any cracked blade. This
amendment is prompted by another report of a cracked blade since the
issuance of the existing AD. Two of the three occurrences of cracked
blades involved the loss of the tail rotor and 90-degree gearbox. The
actions specified by this AD are intended to prevent fatigue failure of
the blade, loss of the tail rotor, and subsequent loss of control of
the helicopter.
DATES: Effective January 4, 2000. The incorporation by reference of
certain publications listed in the regulations is approved by the
Director of the Federal Register as of January 4, 2000.
Comments for inclusion in the Rules Docket must be received on or
before February 18, 2000.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 99-SW-64-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
The service information referenced in this AD may be obtained from
Agusta, 21017 Cascina Costa di Samarate (VA), Via Giovanni Agusta 520,
telephone (0331) 229111, fax (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 76137; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Richard A. Monschke, Aerospace
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5116, fax
(817) 222-5961.
SUPPLEMENTARY INFORMATION: On September 18, 1987, the FAA issued AD 87-
03-14 R2, Amendment 39-5742, Docket No. 87-ASW-2 effective October 14,
1987, to require inspecting the blades for a crack and replacing any
cracked blade with an airworthy blade. That action was prompted by two
reports of cracked blades and separation of a tail rotor gearbox. That
condition, if not corrected, could result in fatigue failure of a
blade, loss of the tail rotor, and subsequent loss of control of the
helicopter.
Since the issuance of that AD, another case has been reported of
failure of a blade, P/N 109-0132-02, followed by the loss of the tail
rotor and 90-degree gearbox assembly. The blade failed due to a crack
in the central area of the blade near the tip of the root doubler.
Agusta S.p.A. issued Bollettino Tecnico 109-110, dated July 28, 1999
(technical bulletin), which supersedes Telegraphic Technical Bulletin
109-5, dated January 27, 1987. The technical bulletin specifies dye-
penetrant inspecting any blade, P/N 109-0132-02 (all dash numbers),
with 400 or more hours TIS, for a crack before further flight and
thereafter at intervals not to exceed 100 hours TIS. The technical
bulletin also specifies visually inspecting each blade before the first
flight of each day and replacing any cracked blade. In the technical
bulletin, the manufacturer reemphasizes the importance of performing a
detailed inspection of the blade by publishing additional procedures
and requirements for personnel conducting the inspections. Agusta
S.p.A. is attempting to develop an improved blade, which would provide
a basis for terminating the inspection requirement.
Since an unsafe condition has been identified that is likely to
exist or develop on other Agusta Model A109A and A109A II helicopters
of the same type design, this AD supersedes AD 87-03-14 R2, effective
October 14, 1987. This AD requires dye-penetrant inspecting any blade,
P/N 109-0132-02 (all dash numbers), with 400 or more hours TIS, for a
crack before further flight and thereafter at intervals not to exceed
100 hours TIS. This AD also requires visually inspecting each blade
before the first flight of each day and replacing any cracked blade
with an airworthy blade. The actions are required to be accomplished in
accordance with the technical bulletin described previously. The short
compliance time involved is required because the previously described
critical unsafe condition can adversely affect the controllability and
structural integrity of the helicopter. Therefore, dye-penetrant
inspecting each blade for a crack is required before further flight 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 54 helicopters will be affected by this AD,
that it will take approximately 2.5 work hours to accomplish the
inspections, and that the average labor rate is $60 per work hour.
Based on these figures, the total cost impact of the AD on U.S.
operators is estimated to be $48,600 assuming 6 dye penetrant
inspections a year.
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
[[Page 71010]]
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, both before and after the closing date for comments, 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 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. 99-SW-64-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
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.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-5742 and by
adding a new airworthiness directive (AD), Amendment 39-11472, to read
as follows:
AD 99-26-13 Agusta S.p.A.: Amendment 39-11472. Docket No. 99-SW-64-
AD. Supersedes Priority Letter AD 87-03-14 R2, Amendment 39-5742,
Docket No. 87-ASW-2.
Applicability: Model A109A and A109A II helicopters, with tail
rotor blade (blade), part number (P/N) 109-0132-02-all dash numbers,
with 400 or more hours time-in-service (TIS), 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 (c) 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 as indicated, unless accomplished
previously.
To prevent fatigue failure of a blade, loss of the tail rotor,
and subsequent loss of control of the helicopter, accomplish the
following:
(a) Before further flight, dye-penetrant inspect each blade for
a crack in accordance with the Compliance Instructions, Part I, of
Agusta S.p.A. Bollettino Tecnico 109-110, dated July 28, 1999
(technical bulletin). Thereafter, at intervals not to exceed 100
hours TIS, dye-penetrant inspect each blade for a crack in
accordance with the Compliance Instructions, Part III, of the
technical bulletin. If a crack is found, replace the cracked blade
with an airworthy blade before further flight.
(b) Before the first flight each day, visually inspect each
blade for a crack using a 3 to 5 power magnifying glass in
accordance with the Compliance Instructions, Part II, of the
technical bulletin. If a crack is found, replace the cracked blade
with an unairworthy blade before further flight.
(c) 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, FAA, Rotorcraft
Directorate. 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.
(d) Special flight permits will not be issued.
(e) The inspections shall be done in accordance with the
Compliance Instructions of Agusta S.p.A. Bollettino Tecnico 109-110,
dated July 28, 1999. 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), Via Giovanni Agusta 520, telephone
(0331) 229111, fax (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.
(f) This amendment becomes effective on January 4, 2000.
Note 3: The subject of this AD is addressed in Registro
Aeronautico Italiano, Italy, AD 99-325, dated August 2, 1999.
Issued in Fort Worth, Texas, on December 9, 1999.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-32580 Filed 12-17-99; 8:45 am]
BILLING CODE 4910-13-U
