[Federal Register Volume 67, Number 22 (Friday, February 1, 2002)]
[Rules and Regulations]
[Pages 4895-4896]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-2423]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-SW-38-AD; Amendment 39-12625; AD 2002-01-30]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model SE 3130, SE
313B, SA 315B, SE 3160, SA 316B, SA 316C, SA 3180, SA 318B, SA 318C,
and SA 319B 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
Eurocopter France (ECF) Model SE 3130, SE 313B, SA 315B, SE 3160, SA
316B, SA 316C, SA 3180, SA 318B, SA 318C, and SA 319B helicopters with
a certain main gearbox (MGB) installed. This action requires inspecting
the magnetic plug for magnetic particles at specified intervals in
addition to the MGB inspections currently required. This AD also
requires, within 50 hours time-in-service (TIS), dye-penetrant
inspecting the MGB bevel gear for a crack, and if a crack is found,
replacing the cracked bevel gear with an airworthy bevel gear before
further flight. This amendment is prompted by an MGB failure due to a
cracked bevel gear. This condition, if not corrected, could result in
failure of the MGB, loss of the main rotor drive, and subsequent loss
of control of the helicopter.
DATES: Effective February 19, 2002.
Comments for inclusion in the Rules Docket must be received on or
before April 2, 2002.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 2001-SW-38-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].
FOR FURTHER INFORMATION CONTACT: Ed Cuevas, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations Group, Fort Worth, Texas
76193-0111, telephone (817) 222-5355, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION: The Direction Generale De L'Aviation Civile
(DGAC), the airworthiness authority for France, notified the FAA that
an unsafe condition may exist on ECF Model SE 3130, SE 313B, SA 315B,
SE 3160, SA 316B, SA 316C, SA 3180, SA 318B, SA 318C, and SA 319B
helicopters with certain MGBs installed. The DGAC advises of the
discovery of a crack on the bevel gear installed on an Alouette
helicopter, which may cause failure of the MGB, subsequent loss of the
main rotor drive, and an auto-rotation landing.
ECF has issued Alert Telex 01.67 and 01.32, dated April 20, 2001,
and Alert Service Bulletins 01.32 and 01.67, both dated July 18, 2001,
specifying a dye-penetrant inspection of both bevel gear faces in the
coupling areas of the bevel gear and the bevel gear housing assembly of
the MGB. The DGAC classified these service bulletins as mandatory and
issued ADs 2001-149-044(A) R1, 2001-178-058(A) R1, and 2001-179-061(A)
R1, all dated August 8, 2001, to ensure the continued airworthiness of
these helicopters in France.
These helicopter models are manufactured in France 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, the DGAC has kept the FAA informed of
the situation described above. The FAA has examined the findings of the
DGAC, reviewed all available information, and determined that AD action
is necessary for products of this type design that may operate in the
United States.
This unsafe condition may exist or develop on other helicopters of
the same type designs with these certain MGBs installed. We are issuing
this AD to prevent failure of an MGB due to a cracked bevel gear, loss
of the main rotor drive, and subsequent loss of control of the
helicopter. This AD requires inspecting the MGB magnetic plug for metal
particles at intervals not to exceed 10 hours TIS. This AD also
requires, within 50 hours TIS, dye-penetrant inspecting the bevel gear
for a crack and, if a crack is found, replacing the unairworthy bevel
gear with an airworthy bevel gear before further flight. Replacing a
cracked bevel gear is terminating action for the requirements of this
AD.
None of the eight MGBs affected by this action are currently
installed on helicopters on the U.S. Register. All helicopters included
in the applicability of this rule that have an affected MGB installed
are currently operated by non-U.S. operators under foreign registry;
therefore, they are not directly affected by this AD action. However,
the FAA considers that this rule is necessary to ensure that the unsafe
condition is addressed in the event that any of these affected MGBs are
imported and installed on helicopters on the U.S. Register in the
future.
Should an affected MGB be imported and installed on a helicopter on
the U.S. Register in the future, it would require approximately \1/2\
work hour to review the records for a certain MGB. If the affected MGB
is present, the FAA estimates that it would take 30 work hours per
helicopter to inspect the bevel gear. The average labor rate is $60 per
work hour. Required parts would cost approximately $14,500 per
helicopter to replace a cracked bevel gear. Based on these figures, the
total cost impact of this AD would be $16,330, assuming one helicopter
requires replacement of the bevel gear.
Since this AD action does not affect any helicopter that is
currently on the U.S. register, it has no adverse economic impact and
imposes no additional burden on any person. Therefore, notice and
public procedures hereon are unnecessary and the amendment may be made
effective in less than 30 days after publication in the Federal
Register.
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.
[[Page 4896]]
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. 2001-SW-38-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 notice and prior public comment are
unnecessary in promulgating this regulation; therefore, it can be
issued immediately to correct an unsafe condition in aircraft since
none of these model helicopters are registered in the United States.
The FAA has also determined that this regulation 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 CFR Part 39
Air transportation, Aircraft, Aviation safety, 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 adding a new airworthiness directive
to read as follows:
2002-01-30 Eurocopter France: Amendment 39-12625. Docket No. 20.1-
SW-38-AD.
Applicability: Model SE 3130, SE 313B, SA 315B, SE 3160, SA
316B, SA 316C, SA 3180, SA 318B, SA 318C, and SA 319B, helicopters
with a main gearbox (MGB), part number 319A62-00-000.4 with serial
number M1242, M2194, M2516, NT3488, NT3563, 3-2888, 3-3091, or 3-
11336, 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 (d) 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 failure of the MGB due to a cracked bevel gear, loss
of the main rotor drive, and subsequent loss of control of the
helicopter, accomplish the following:
(a) At intervals not to exceed 10 hours time-in-service (TIS),
inspect the MGB magnet plug for metal particles. This 10-hour
inspection is in addition to those currently required by the
maintenance manual.
(b) Within 50 hours TIS, dye-penetrant inspect both faces of the
MGB bevel gear in the coupling area of the bevel gear shaft and in
the coupling area of the bevel gear housing for a crack. If a crack
is found, replace the unairworthy part with an airworthy part before
further flight.
Note 2: Eurocopter France Alert Service Bulletins 01.32 and
01.67, both dated July 18, 2001, pertain to the subject of this AD.
(c) Completing the dye-penetrant inspection required by
paragraph (b) of this AD and finding no cracks or replacing the
bevel gear with an airworthy bevel gear is terminating action for
the requirements of this AD.
(d) 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Regulations Group.
(e) Special flight permits may be issued in accordance with 14
CFR 21.197 and 21.199 to operate the helicopter to a location where
the requirements of this AD can be accomplished.
(f) This amendment becomes effective on February 19, 2002.
Note 4: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) ADs 2001-149-044(A) R1, 2001-
178-058(A) R1, and 2001-179-061(A) R1, all dated August 8, 2001.
Issued in Fort Worth, Texas, on January 22, 2002.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-2423 Filed 1-31-02; 8:45 am]
BILLING CODE 4910-13-M