Airworthiness Directives; Eurocopter France Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and EC130 B4 Helicopters

[Federal Register Volume 67, Number 54 (Wednesday, March 20, 2002)]
[Rules and Regulations]
[Pages 12856-12858]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-6627]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-SW-09-AD; Amendment 39-12681; AD 2002-03-52]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS350B, 
AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, 
AS355F, AS355F1, AS355F2, AS355N, and EC130 B4 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD) 2002-03-52, sent previously to 
all known U.S. owners and operators of Eurocopter France (ECF) 
helicopters by individual letters. This AD requires checking for a gap 
between the adhesive bead and the metal bushing bonded on each STARFLEX 
star arm end (arm end) and, if a gap is found, replacing the STARFLEX 
with an airworthy part. This AD is prompted by reports of bonding 
failure between the metal bushing and the arm end that led to severe 
vibrations resulting in several emergency landings. The actions 
specified in this AD are intended to detect bonding failure between the 
metal bushing and each arm end, severe lateral vibrations, and 
subsequent loss of control of the helicopter.

DATES: Effective April 4, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before April 19, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2002-SW-09-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: [email protected].

FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, 
Texas 76193-0111, telephone (817) 222-5130, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: On February 6, 2002, the FAA issued 
Emergency AD (EAD) 2002-02-51, which required checking for a gap 
between the adhesive bead and the metal bushing on each arm end and, if 
a gap was found, replacing the STARFLEX. After issuing that EAD, we 
discovered the inadvertent omission of a STAFFLEX part number (P/N) 
from the applicability. That omission created an undue economic burden 
to the owners and operators of a significant percentage of the affected 
helicopters. That omission could have also created confusion to the 
personnel checking this flight critical part because there are a number 
of different STARFLEX configurations installed on the affected model 
helicopters. This condition, if not corrected, could have resulted in 
failure of the operators to properly conduct the check, failure to 
detect a gap between the adhesive bead and the metal bushing on the arm 
end, severe lateral vibrations, and subsequent loss of control of the 
helicopter. Therefore, to eliminate any confusion, the FAA issued 
superseding EAD 2002-03-52 on February 8, 2002, which contains the same 
requirements as EAD 2002-02-51 but limits the applicability of this AD 
to those helicopters that have STARFLEX, P/N 350A31-1916-00, installed.
    The Direction Generale De L'Aviation Civile (DGAC), the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on these helicopter models. The DGAC advises of 
several occurrences of rapid bonding failure of the metal bushing 
installed on the arm ends, severe vibrations, and some emergency 
landings.

[[Page 12857]]

    ECF has issued Alert Telex Nos. 05.00.38, 05.00.37R1, and 
05.A.001R1, dated November 13, 2001 (Telex). The Telex specifies 
checking for a gap between the adhesive bead and the metal bushing 
bonded on each arm end. ECF is currently analyzing modifications to 
this assembly. The DGAC classified this Telex as mandatory and issued 
AD Nos. 2001-557-086(A) R1, 2001-558-064(A) R1, and 2001-559-002(A) R1, 
all dated November 28, 2001, to ensure 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 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral 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.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type designs registered in the United States. 
Therefore, the FAA issued Emergency AD 2002-03-52 to require, at 
specified intervals, checking for a gap between the adhesive bead and 
the metal bushing bonded on each of the arm ends and, if a gap is 
found, before further flight, replacing any STARFLEX with an airworthy 
part.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability or structural integrity of the helicopter. Therefore, 
checking for a gap between the adhesive bead and the metal bushing is 
required before each start of the engines and thereafter at intervals 
not to exceed 4 hours time-in-service, and this AD must be issued 
immediately.
    An owner/operator (pilot) may perform the visual check required by 
paragraph (a) of this AD and must enter compliance with this AD into 
the helicopter maintenance records in accordance with 14 CFR 43.11 and 
91.417(a)(2)(v). This AD allows a pilot to perform this check because 
it involves only a visual check for a gap between the adhesive bead and 
the metal bushing on each arm end and can be performed equally well by 
a pilot or a mechanic.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD immediately effective by individual letters 
issued on February 8, 2002, to all known U.S. owners and operators of 
these helicopters. These conditions still exist, and the AD is hereby 
published in the Federal Register as an amendment to 14 CFR 39.13 to 
make it effective to all persons.
    The FAA estimates that 30 helicopters will be affected by this AD, 
that it will take approximately 0.1 work hour to inspect the adhesive 
bead of the metal bushing bonded on each arm end, and that the average 
labor rate is $60 per work hour. Based on these figures, the total cost 
impact of the AD on U.S. operators is estimated to be $6 per helicopter 
and $180 for one inspection of the fleet. Assuming 10 additional 
inspections per week for all helicopters, the fleet cost per year will 
be $93,600.

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 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 mailed 
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. 2002-SW-09-AD.'' The postcard will be date 
stamped and returned to the commenter.
    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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:

2002-03-52  Eurocopter France: Amendment 39-12681. Docket No. 2002-
SW-09-AD. Supersedes Emergency AD 2002-02-51, Docket No. 2002-SW-02-
AD.
    Applicability: Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, 
AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, 
and EC130 B4 helicopters, with STARFLEX, part number 350A31-1916-00, 
installed, certificated in any category.

    Note 1: This AD applies to each helicopter identified in the 
preceding applicability

[[Page 12858]]

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 (d) 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 before each start of the engines and 
thereafter at intervals not to exceed 4 hours time-in-service.
    To detect bonding failure between the metal bushing and each 
STARFLEX star arm end (arm end), which could result in severe 
lateral vibrations and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Check for a gap between the adhesive bead and the metal 
bushing bonded on each of the three arm ends.

    Note 2: Alert Telex Nos. 05.00.38, 05.00.37 R1, and 05.A.001 R1, 
dated November 13, 2001, pertain to the subject of this AD.

    (b) An owner/operator (pilot) may perform the visual check 
required by paragraph (a) of this AD and must enter compliance with 
this AD into the helicopter maintenance records in accordance with 
14 CFR 43.11 and 91.417(a)(2)(v). This AD allows a pilot to perform 
this check because it involves only a visual check for a gap between 
the adhesive bead and the bushing on each arm end and can be 
performed equally well by a pilot or a mechanic.
    (c) If you find a gap between the adhesive bead and the metal 
bushing, replace the STARFLEX with an airworthy part before further 
flight.
    (d) 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, Regulations Group, 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, Regulations Group.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (e) Special flight permits will not be issued.
    (f) This amendment becomes effective on April 4, 2002.

    Note 4: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD Nos. 2001-557-086(A) R1, 
2001-558-064(A) R1, and 2001-559-002(A) R1, all dated November 28, 
2001.


    Issued in Fort Worth, Texas, on March 11, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-6627 Filed 3-19-02; 8:45 am]
BILLING CODE 4910-13-U

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