[Federal Register Volume 63, Number 69 (Friday, April 10, 1998)]
[Rules and Regulations]
[Pages 17674-17676]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-9477]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-SW-27-AD; Amendment 39-10462; AD 98-08-13]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model SA 330F, G, and
J, and AS 332C, L, L1, and L2 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 SA 330F, G, and J, and AS
332C, L, L1, and L2 helicopters. This action requires daily inspections
of the root of each tail rotor head pitch change spider arm (spider
arm) for cracks, and an inspection of the tail rotor head pitch change
spider (spider) for cracks and fretting corrosion. A terminating action
for the requirements of this AD is the installation of an airworthy
modified spider, an airworthy replacement spider, or an airworthy
repaired spider. This amendment is prompted by one in-service report of
fatigue cracking on a Model AS 332 helicopter. This condition, if not
corrected, could result in failure of the spider arm, loss of control
of the tail rotor blade, and subsequent loss of control of the
helicopter.
DATES: Effective April 27, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 27, 1998.
Comments for inclusion in the Rules Docket must be received on or
before June 9, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 97-SW-27-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
The service information referenced in this AD may be obtained from
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas
75053-4005, telephone (972) 641-3460, fax (972) 641-3527. This
information may be examined 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.
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 SA 330F, G, and J, and AS 332C, L, L1, and L2 helicopters.
The DGAC advises that fatigue cracking in spider, part number (P/N)
332A330039.20 or .21, for Model AS 332 helicopters, and P/N
332A330039.20 or .21, or P/N 330A330104.20 or .21 for Model SA 330
helicopters, could result in failure of the spider arm, loss of control
of the tail rotor blade and subsequent loss of control of the
helicopter.
Eurocopter France has issued Eurocopter France SA 330 Service
Bulletin (SB) No. 01.52 R1, Revision No. 1, and Eurocopter France AS
332 SB No.
[[Page 17675]]
01.00.43, Revision No. 1, both dated February 14, 1996, which specify a
daily check of the root of the spider arm for cracks, and specify
detailed inspections of the entire spider arm for cracks or fretting
corrosion within 250 hours time-in-service (TIS). The DGAC classified
these service bulletins as mandatory and issued AD 95-262-056(B)R1 for
the Model AS 332 helicopters, and AD 95-263-073(B)R1 for the Model SA
330 helicopters, both dated April 10, 1996, 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 these type designs 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 SA 330F, G, and J,
and AS 332C, L, L1, and L2 helicopters of the same type design
registered in the United States, this AD is being issued to prevent
failure of the spider arm, loss of control of the tail rotor blade, and
subsequent loss of control of the helicopter. This AD requires a daily
inspection, prior to the first flight of the day, of the root of each
spider arm for cracks, and requires a detailed inspection of the entire
spider arm for cracks and fretting corrosion within 250 hours TIS. A
terminating action is provided in the AD by installing an airworthy
modified spider, an airworthy replacement spider, or an airworthy
repaired spider. The actions are required to be accomplished in
accordance with the service bulletins described previously. This AD
differs from the DGAC AD's in the required inspection schedule and in
the type of inspection that is required. The DGAC AD's require
inspections after the last flight of each day. The FAA considers that
the most critical time to perform the inspections would be before the
first flight of each day and has worded this AD as such. Also, the DGAC
AD's require a visual inspection and, if it cannot be determined
whether a crack is present, a subsequent dye-penetrant inspection; this
AD requires a dye-penetrant inspection and doesn't allow the option of
an initial visual inspection.
None of the Model SA 330 or AS 332 helicopters affected by this
action are on the U.S. Register. All helicopters included in the
applicability of this rule currently are 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 subject helicopters are imported and placed on the U.S.
Register in the future.
Should an affected helicopter be imported and placed on the U.S.
Register in the future, it would require approximately 4.0 work hours
to accomplish the required inspections, and 1.5 work hours to replace a
spider arm at an average labor charge of $60 per work hour. Required
parts would cost $100 each. Based on these figures, the cost impact of
this AD to inspect and replace all 5 spider arms would be $1,190 per
helicopter.
Since this AD action does not effect 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.
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-27-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 notice and prior public comment are
unnecessary in promulgating this regulation and 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,
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:
[[Page 17676]]
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 98-08-13 Eurocopter France: Amendment 39-10462. Docket No. 97-
SW-27-AD.
Applicability: Model SA 330F, G, and J helicopters with tail
rotor head pitch change spider arm (spider arm), part number (P/N)
330A330104.20 or .21, or 332A330039.20 or .21, installed and Model
AS 332C, L, L1, and L2 helicopters with spider arm, P/N
332A330039.20 or .21 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 (e) 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 as indicated, unless accomplished
previously.
To prevent failure of a spider arm, loss of control of the tail
rotor blade, and subsequent loss of control of the helicopter,
accomplish paragraphs (a) through (d) in accordance with the
specified paragraphs of Eurocopter France Service Bulletin No. 01.52
R1, Revision No. 1, for Model SA 330 helicopters, or Eurocopter
France AS 332 Service Bulletin No. 01.00.43, Revision No. 1, for
Model AS 332 helicopters, both dated February 14, 1996:
(a) Prior to the first flight of each day, inspect the root of
each of the spider arms for cracks in accordance with paragraph
1.C.1) of the applicable service bulletin.
(b) Within 250 hours time-in-service (TIS), or prior to the
installation of a replacement spider arm, whichever occurs earlier,
disassemble the tail rotor head and inspect each spider arm for
cracks and fretting corrosion in accordance with Paragraph 2.B of
the Accomplishment Instructions of the applicable service bulletin.
The inspections in paragraph (a) of this AD are no longer required
after accomplishment of the inspection specified in this paragraph.
(c) If any crack is found, replace the spider arm with an
airworthy spider arm in accordance with Paragraph 2.B.1)b)1) of the
Accomplishment Instructions of the applicable service bulletin.
Replacement of a cracked spider arm with an airworthy spider arm
constitutes terminating action for the requirements of this AD.
Note 2: Care should be taken to ensure that Revision 1 of the
referenced service bulletins is used to set the shim thickness when
attaching the spider arm upon reassembly. Operators who have
complied with the initial release of the referenced service
bulletins and not with Revision 1 of the service bulletins will not
be in compliance with this AD.
(d) If fretting corrosion is found as a result of the inspection
in paragraph (b) of this AD, either repair the fretting corrosion in
accordance with paragraph 2.B.1)b)2) of the Accomplishment
Instructions of the applicable service bulletin; or, if the fretting
corrosion is not repairable in accordance with the applicable
service bulletin, replace the spider arm with an airworthy spider
arm in accordance with paragraph 2.B of the Accomplishment
Instructions of the applicable service bulletin. Repair of fretting
corrosion in accordance with this paragraph or replacement of the
spider arm with an airworthy spider arm in accordance with the
applicable service bulletin constitutes terminating action for the
requirements of this AD.
(e) Installation of a spider that has been modified in
accordance with MOD 330A07-66131 (for Model SA 330F, G, and J
helicopters), or AMS 332A07-66151 (for Model AS 332C, L, L1, and L2
helicopters) constitutes a terminating action for the requirements
of this AD.
(f) 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Standards Staff.
(g) 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.
(h) The inspections and replacements shall be done in accordance
with Eurocopter France SA 330 Service Bulletin (SB) No. 01.52 R1,
Revision No. 1, for Model SA 330 helicopters, or Eurocopter France
AS 330 SB No. 01.00.43, Revision No. 1, for Model AS 332
helicopters, both dated February 14, 1996. 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, 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.
(i) This amendment becomes effective on April 27, 1998.
Note 4: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD 95-262-056(B)R1 for the
model AS 332 helicopters, and AD 95-263-073(B)R1 for the Model SA
330 helicopters, both dated April 10, 1996.
Issued in Fort Worth, Texas, on April 3, 1998.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-9477 Filed 4-9-98; 8:45 am]
BILLING CODE 4910-13-U
