[Federal Register Volume 63, Number 231 (Wednesday, December 2, 1998)]
[Rules and Regulations]
[Pages 66418-66420]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-31858]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-41-AD; Amendment 39-10921; AD 98-24-35]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS-350B, B1,
B2, BA, C, D, D1, and AS 355E, F, F1, F2, and N Helicopters
AGENCY: Federal Aviation Administration, DOT.
[[Page 66419]]
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, BA, C, D, D1,
and AS 355E, F, F1, F2, and N helicopters. This action requires
measuring the tail rotor pitch change control rod (control rod)
outboard spherical bearing for radial and axial play. If the play
exceeds 0.008-inch, replacing the control rod with an airworthy control
rod is required. This amendment is prompted by one accident and one
incident. Investigations revealed a broken control rod on the
helicopter involved in the accident and a severely worn control rod on
the helicopter involved in the incident. This condition, if not
corrected, could result in separation of the outboard spherical bearing
ball from its outer race, rubbing of the body of the control rod
against the tail rotor blade pitch horn clevis, failure of the control
rod, and loss of control of the helicopter.
DATES: Effective December 17, 1998.
Comments for inclusion in the Rules Docket must be received on or
before February 1, 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-41-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT: Mr. 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: This amendment was prompted by an accident,
which occurred in November 1996, and an incident, which occurred in
August 1997, involving Model AS-350B2 helicopters offshore over the
Gulf of Mexico. The DGAC, although notified by the FAA of both the
accident and incident, has not issued an AD on this subject. There were
two other unconfirmed incidents cited by the National Transportation
Safety Board (based on manufacturer's reports) involving the same
control rod, part number (P/N) 350A33-2145-01.
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. The FAA has
determined that AD action is necessary for products of this type design
certified for operation in the United States.
Since an unsafe condition has been identified that is likely to
exist or develop on other Eurocopter France Model AS-350B, B1, B2, BA,
C, D, D1, and 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 separation of the outboard spherical bearing ball from its
outer race, rubbing of the body of the control rod against the tail
rotor blade pitch horn clevis, failure of the control rod, and loss of
control of the helicopter. The short compliance time involved is
required because the previously described critical unsafe condition can
adversely affect the controllability of the helicopter. Therefore,
measuring the control rod outboard spherical bearing radial and axial
play is required within 50 hours time-in-service, 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.
Cost Impact
The FAA estimates that 507 helicopters will be affected by this AD,
that it will take approximately 1 work hour, and that the average labor
rate is $60 per work hour. Required parts will cost approximately
$2,376 per helicopter. Based on these figures, the total cost impact of
this AD on U.S. operators is estimated to be $1,235,052 to perform the
measurement and to replace both control rods on each helicopter in the
fleet.
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, 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-41-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
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, 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
[[Page 66420]]
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 98-24-35 Eurocopter France: Amendment 39-10921. Docket No. 98-
SW-41-AD.
Applicability: Eurocopter France Model AS-350B, B1, B2, BA, C,
D, D1, and AS 355E, F, F1, F2, and N helicopters, with tail rotor
pitch change control rod (control rod), part number (P/N) 350A33-
2145-01, 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 (b) 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 50 hours time-in-service (TIS) after
the effective date of this AD, unless accomplished previously, and
thereafter at intervals not to exceed 50 hours TIS.
To prevent separation of the outboard spherical bearing ball
from its outer race, rubbing of the body of the control rod against
the tail rotor blade pitch horn clevis, failure of the control rod,
and loss of control of the helicopter, accomplish the following:
(a) Using a dial indicator, measure the axial and radial play of
the outboard spherical bearing on the control rod. If the play
exceeds 0.008-inch, replace the control rod with an airworthy
control rod.
(b) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used when 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.
(c) 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.
(d) This amendment becomes effective on December 17, 1998.
Issued in Fort Worth, Texas, on November 19, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-31858 Filed 12-1-98; 8:45 am]
BILLING CODE 4910-13-U
