AD Amdt-39-11084

[Federal Register Volume 64, Number 55 (Tuesday, March 23, 1999)]
[Rules and Regulations]
[Pages 13886-13889]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 99-6976]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-46-AD; Amendment 39-11084; AD 99-07-02]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS 332C, L, L1, 
and L2 Helicopters and Model SA 330F, G, and J 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 332C, L, L1, and L2 
helicopters and Model SA 330F, G, and J helicopters. This action 
requires inspecting the position and bonding of the main rotor blade 
(blade) leading edge stainless steel protective strips (strips) that 
were replaced by C.T.I. Dallas. This amendment is prompted by the 
discovery of a strip that was both mislocated and improperly bonded. 
The strip had been replaced by C.T.I. Dallas. This condition, if not 
corrected, could result in failure of the blade and subsequent loss of 
control of the helicopter.

DATES: Effective April 7, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before May 24, 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-46-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.

FOR FURTHER INFORMATION CONTACT: 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, has notified 
the FAA that an unsafe condition may exist on Eurocopter France Model 
AS 332C, L, L1, and L2 helicopters and Model SA 330F, G, and J 
helicopters. The DGAC advises that, upon examination of a blade that 
had been repaired by C.T.I. Dallas, anomalies were found in both the 
installation and the bonding of the strip that could affect aircraft 
safety.
    Eurocopter France has issued Eurocopter France SA 330 Service 
Bulletin No. 05.85 and Eurocopter France AS 332 Service Bulletin No. 
05.00.43, both dated August 27, 1997, which specify checking the 
position and bonding of the blade strips. The DGAC classified these 
service bulletins as mandatory and issued AD 97-293-078(AB) and AD 97-
292-064(AB), both dated October 8, 1997, 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 5 helicopters will be affected by this AD, 
that it will take approximately 0.4 work hours to accomplish the 
initial inspection, 2 work hours to accomplish each of 100 repetitive 
inspections of each helicopter, and 4 work hours to replace each blade, 
and that the average labor rate is $60 per work hour. Required parts 
will cost approximately $25,000 per rotor blade. Based on these 
figures, the total cost impact of the AD on U.S. operators is estimated 
to be $85,360, assuming one blade on one helicopter is replaced and 
that there will be a total of 100 repetitive inspections required on 
each helicopter by this AD.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Eurocopter France Model AS 332C, L, L1, and 
L2 helicopters and Model SA 330F, G, and J helicopters of the same type 
designs registered in the United States, this AD is being issued to 
prevent failure of the blade and subsequent loss of control of the 
helicopter. This AD requires, within 10 hours time-in-service (TIS), 
inspecting strips that were replaced by C.T.I. Dallas for correct 
position. If the inspection indicates an incorrectly-positioned strip, 
the blade must be removed and replaced with an airworthy blade. This AD 
also requires, within 100 hours TIS, and thereafter at intervals not to 
exceed 100 hours TIS, inspecting the strips for proper bonding. The 
actions are required to be accomplished in accordance with the service 
bulletins described previously. 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 position and bonding of the strips is required prior to 
further flight, 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

[[Page 13887]]

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-46-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 99-07-02  Eurocopter France: Amendment 39-11084. Docket No. 98-
SW-46-AD.
    Applicability: Model SA 330F, G, and J helicopters, with main 
rotor blades, part number (P/N) 330A11-0020 (all dash numbers), P/N 
330A11-0022 (all dash numbers), or P/N 330A11-0027 (all dash 
numbers), installed, and Model AS 332C, L, L1, and L2 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 
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 (c) 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 detect a mislocated or improperly bonded main rotor blade 
(blade) leading edge stainless steel protective strip (strip), which 
could result in failure of the blade and subsequent loss of control 
of the helicopter, accomplish the following:
    (a) Within 10 hours time-in-service (TIS):
    (1) Determine from helicopter records or log cards if the blade 
strips were replaced by C.T.I. Dallas. The helicopter records or log 
cards will have ``CTID'' stamped on them if C.T.I. Dallas replaced 
the strips. Blades with strips that were not replaced by C.T.I. 
Dallas need not comply with the remaining paragraphs of this AD.
    (2) Inspect the blade strips for correct positioning on each 
main rotor blade by measuring the distance from the tip cap-blade 
junction as shown in Figure 1. This distance must be 2228 mm plus or 
minus 15 mm (87.7 inches plus or minus 0.6 inch). If the strip is 
incorrectly positioned, remove the blade and replace it with an 
airworthy blade within 100 hours TIS (see Figure 1).

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    (b) Within 100 hours TIS, and thereafter at intervals not to 
exceed 100 hours TIS, inspect the strips for correct bonding using a 
bonding check by sound (tapping test). If a defect is found that is 
outside the tolerance limits, remove the blade and replace it with 
an airworthy blade.
    (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 2: 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 April 7, 1999.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 97-293-078(AB) and AD 97-
292-064(AB), both dated October 8, 1997.

    Issued in Fort Worth, Texas, on March 12, 1999.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-6976 Filed 3-22-99; 8:45 am]
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