[Federal Register Volume 63, Number 49 (Friday, March 13, 1998)]
[Rules and Regulations]
[Pages 12408-12410]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-6449]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-SW-33-AD; Amendment 39-10390; AD 98-06-12]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS-350B, BA,
B1, B2, 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, BA, B1, B2, and D
helicopters, and Model AS 355E, F, F1, F2, and N helicopters. This
action requires replacing certain tailboom attachment bolts located
above the cargo compartment floor. This amendment is prompted by two
reports of attachment bolts' strength properties not meeting design
specifications during manufacture. The actions specified in this AD are
intended to identify and remove the weaker bolts and to prevent the
separation of the tailboom from the helicopter, and subsequent loss of
control of the helicopter.
DATES: Effective March 30, 1998. Comments for inclusion in the Rules
Docket must be received on or before May 12, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of Regional Counsel, Southwest Region,
Attention: Rules Docket No. 97-SW-33-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT: Mr. Mike Mathias, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5123, 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, BA, B1, B2, and D helicopters, and Model AS 355E,
F, F1, F2, and N helicopters. The DGAC advises that due to the
discovery of the installation of tailboom attachment bolts in the
affected model helicopters which do not meet metallurgical design
requirements, replacement of certain attachment bolts is required
within 100 flying hours.
Eurocopter France has issued Eurocopter France Service Telex No.
00031/00153/97, dated June 2, 1997 (Eurocopter France AS 350 Service
Telex No. 01.00.46 and Eurocopter France AS 355 Service Telex No.
01.00.43), which specifies checking the marking on the heads of the 23
attachment bolts of the tailboom-to-aircraft junction located above the
baggage compartment floor, and scrapping all attachment bolts that are
marked with the letter ``M'' above the designation ``BC''; and,
replacing the unairworthy attachment bolts with airworthy attachment
bolts, in accordance with the special instructions given in Maintenance
Manual (MET) work card 53.00.00.402, paragraph 4. Replacement bolts
must be marked with a symbol other than the letter ``M''. The DGAC
classified this service telex as mandatory and issued DGAC AD 97-147-
072(AB), and AD 97-146-054(AB), both dated July 16, 1997, in order to
assure the continued airworthiness of these helicopters in France.
This helicopter model is manufactured in France and is 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.
Since an unsafe condition has been identified that is likely to
exist or develop on other Eurocopter France Model AS-350B, BA, B1, B2,
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 require the removal of understrength tailboom attachment
bolts to prevent separation of the tailboom, and subsequent loss of
control of the helicopter. This AD requires removal and replacement of
certain tailboom attachment bolts within 10 hours time-in-service for
[[Page 12409]]
helicopters that were delivered from the manufacturer prior to May 16,
1997, or were overhauled prior to May 16, 1997, or had any tailboom
attachment bolts, part number (P/N) 22201BC060008L, replaced after July
1, 1994. If the helicopter meets either of those criteria, the AD
requires an inspection of the marking on each of the 23 attachment
bolts that are located above the baggage compartment floor, and
replacement of any attachment bolt that is marked with the letter ``M''
above the designation ``BC'' on the head of the attachment bolts with
an airworthy attachment bolt marked with a letter other than ``M''. The
short compliance time involved is required because the previously
described critical unsafe condition can adversely affect the structural
integrity of the helicopter. Therefore, the replacement of the
attachment bolts is required within 10 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.
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. 97-SW-33-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, 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 98-06-12 Eurocopter France: Amendment 39-10390. Docket No. 97-
SW-33-AD.
Applicability: Model AS-350B, BA, B1, B2, and D helicopters, and
Model AS 355E, F, F1, F2, and N helicopters, 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 (c) 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 10 hours time-in-service (TIS),
unless accomplished previously.
To identify and remove the weaker bolts and to prevent the
separation of the tailboom from the helicopter, and subsequent loss
of control of the helicopter, accomplish the following:
(a) For helicopters that either were delivered from the
manufacturer with zero-time before May 16, 1997, were overhauled
before May 16, 1997, or have had any tailboom attachment bolt
(bolt), part number (P/N) 22201BC06008L, replaced after July 1,
1994:
(1) Inspect the markings on each of the 23 bolts located above
the baggage compartment floor.
(2) Remove any of the 23 bolts, P/N 22201BC06008L, that are
marked with the letter ``M'' above the designation ``BC'' and
replace each of them, one-by-one, with an airworthy bolt, P/N
22201BC06008L, that is marked with a letter other than ``M''. Torque
each replacement bolt to between 67 and 79 inch-lbs. using only new
nuts.
Note 2: These inspections and replacements are not required for
helicopters that were delivered from the manufacturer with zero-time
after May 15, 1997, were overhauled after May 15, 1997, and have had
no bolt, P/N 22201BC06008L, replaced after July 1, 1994.
Note 3: The inspection and replacement of the 4 bolts located
below the baggage compartment are not required by this AD.
Note 4: Eurocopter France AS 350 Service Telex No. 01.00.46,
Eurocopter France AD 355 Service Telex No. 01.00.43, and Work Card
53.00.00.402 pertain to this AD.
(b) Replacement of all the bolts, P/N 22201BC06008L, with
airworthy bolts
[[Page 12410]]
marked with a letter other than ``M'' constitutes terminating action
for the requirements of this AD.
(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, 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 5: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Standards Staff.
(d) 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.
(e) This amendment becomes effective on March 30, 1998.
Note 6: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD 97-146-054(AB) and AD 97-
147-072(AB), both dated July 16, 1997.
Issued in Fort Worth, Texas, on March 5, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-6449 Filed 3-12-98; 8:45 am]
BILLING CODE 4910-13-U