[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