[Federal Register Volume 64, Number 78 (Friday, April 23, 1999)]
[Rules and Regulations]
[Pages 19881-19882]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-10053]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-44-AD; Amendment 39-11139; AD 99-09-06]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS-350B, B1,
B2, B3, BA, and D Helicopters, and Model AS 355E, F, F1, F2 and N
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) that
is applicable to Eurocopter France Model AS-350B, B1, B2, B3, BA, and D
helicopters, and Model AS 355E, F, F1, F2 and N helicopters. This
action requires inspecting the tail rotor spider plate bearing
(bearing) for the proper bearing rotational torque, axial play, and for
any brinelling of the bearing. This amendment is prompted by service
difficulty reports citing the need to prematurely replace bearings due
to wear, and by two in-flight incidents of increased tail rotor
vibration levels due to bearing wear. This condition, if not corrected,
could result in seizure of the bearing, loss of tail rotor control and
subsequent loss of control of the helicopter.
DATES: Effective May 10, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 10, 1999.
Comments for inclusion in the Rules Docket must be received on or
before June 22, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 98-SW-44-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT: Shep Blackman, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5296, fax (817)
222-5961.
SUPPLEMENTARY INFORMATION: The Direction Generale De L'Aviation Civile
(DGAC), which is the airworthiness authority for France, recently
notified the FAA that an unsafe condition may exist on Eurocopter
France Model AS-350B, B1, B2, B3, BA, and D helicopters, and Model AS
355E, F, F1, F2 and N helicopters. The DGAC advises that a one-time
measurement of bearing rotational torque and repetitive inspections of
the bearing for axial play, binding, or brinelling is necessary to
prevent seizure of the bearing and loss of control of the helicopter.
Eurocopter France has issued Eurocopter AS 350 Service Bulletin
(SB) No. 05.00.29, applicable to Model AS-350 helicopters, and SB No.
05.00.30, applicable to Model AS 355 helicopters, both dated February
8, 1999. These SB's specify a periodic check of the pitch change spider
plate bearing to prevent any blocking of the bearing. The DGAC
classified these SB's as mandatory and issued AD 1999-084-057(A), and
AD 1999-085-076(A), both dated February 24, 1999, applicable to Model
AS 355 and Model AS-350 helicopters, respectively, in order to assure
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
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness 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 are
certificated for operation in the United States.
The FAA estimates that 507 helicopters will be affected by this AD,
that it will take approximately 1 work hour to accomplish the
inspection, and 4 work hours to replace a bearing, if required, and
that the average labor rate is $60 per work hour. Required parts will
cost approximately $60 per helicopter. Based on these figures, the
total cost impact of the AD on U.S. operators is estimated to be
$182,520 to inspect and replace one bearing in each helicopter in the
fleet.
Since an unsafe condition has been identified that is likely to
exist or develop on other Eurocopter France Model AS-350B, B1, B2, B3,
BA, and D helicopters, and Model AS 355E, F, F1, F2 and N helicopters
of the same type design registered in the United States, this AD is
being issued to prevent seizure of the bearing, loss of tail rotor
control, and subsequent loss of control of the helicopter. This AD
requires, within 50 hours TIS, measuring the bearing rotational torque,
and thereafter at intervals not to exceed 100 hours TIS, inspecting the
bearing for axial play, binding, or brinelling. The short compliance
time involved is required because the previously described critical
unsafe condition can adversely affect the controllability of the
helicopter. Therefore, inspecting the bearing for the proper rotational
torque within the next 50 hours time-in-service (TIS), and for any
bearing roughness at intervals not to exceed 100 hours TIS is 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.
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
[[Page 19882]]
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, 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. 98-SW-44-AD.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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 adding a new airworthiness directive
to read as follows:
AD 99-09-06 Eurocopter France: Amendment 39-11139. Docket No. 98-
SW-44-AD.
Applicability: Eurocopter France Model AS-350B, B1, B2, B3, BA,
and D helicopters, and Model AS 355E, F, F1, F2 and N helicopters,
with tail rotor spider assembly, part number 350A332004-03 or
350A332004-05, 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 seizure of the tail rotor spider plate bearing
(bearing), loss of tail rotor control, and subsequent loss of
control of the helicopter, accomplish the following in accordance
with the specified paragraphs of Eurocopter Service Bulletin (SB)
05.00.29, applicable to Model AS-350 helicopters, or SB 05.00.30,
applicable to Model AS 355 helicopters, both dated February 8, 1999,
as applicable:
(a) Within 50 hours time-in-service, measure the rotational
torque of the bearing using the operational procedure in paragraph
2.B.1 of the Accomplishment Instructions in the applicable SB. If
the rotational load is equal to or greater than 300 grams, replace
the pitch change spider plate assembly with an airworthy pitch
change spider plate assembly before further flight.
(b) At intervals not to exceed 100 hours time-in-service,
measure the axial play, and inspect for rotational binding or
brinelling of the bearing using the operational procedure in
paragraph 2.B.2 of the Accomplishment Instructions in the applicable
SB.
(c) If the bearing fails to meet the airworthiness criteria
stated in paragraph 2.B.3(b) of the Accomplishment Instructions in
the applicable SB, replace the pitch change spider plate assembly
with an airworthy pitch change spider plate assembly before further
flight.
(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, Rotorcraft Standards Staff,
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, Rotorcraft Standards Staff.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Standards Staff.
(e) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the helicopter to a location where
the requirements of this AD can be accomplished.
(f) The measurements and replacements, if necessary, shall be
done in accordance with Eurocopter Mandatory SB 05.00.29, applicable
to Model AS-350 helicopters, or Eurocopter Mandatory SB 05.00.30,
applicable to Model AS 355 helicopters, both dated February 8, 1999,
as applicable. 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 American Eurocopter
Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005,
telephone (972) 641-3460, fax (972) 641-3527. Copies may be
inspected at the FAA, (FAA), Office of the Regional Counsel,
Southwest Region, Attention: Rules Docket No. 98-SW-44-AD, 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.
(g) This amendment becomes effective on May 10, 1999.
Note 3: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD 1999-084-057(A) and AD
1999-085-076(A), both dated February 24, 1999.
Issued in Fort Worth, Texas, on April 14, 1999.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-10053 Filed 4-22-99; 8:45 am]
BILLING CODE 4910-13-U
