Airworthiness Directives; Eurocopter France Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 Helicopters

[Federal Register Volume 67, Number 230 (Friday, November 29, 2002)]
[Rules and Regulations]
[Pages 71097-71098]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-29155]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-34-AD; Amendment 39-12948; AD 2002-23-04]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA-365N, SA-
365N1, AS-365N2, and AS 365 N3 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
the specified Eurocopter France (ECF) model helicopters that requires 
inspecting the 9-degree frame (frame) for the correct edge distance of 
the two attachment holes for the reinforced latch support and for a 
crack and repairing the frame if necessary. This amendment is prompted 
by the detection of a fatigue crack on the left-hand (LH) side of the 
frame during maintenance. The actions specified by this AD are intended 
to prevent failure of the frame due to a crack at the latch support, 
loss of a passenger door, damage to the rotor system, and subsequent 
loss of control of the helicopter.

DATES: Effective January 3, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 3, 2003.

ADDRESSES: 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: Jim Grigg, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, 
Texas 76193-0110, telephone (817) 222-5490, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to 
include an AD for ECF Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 
helicopters was published in the Federal Register on August 14, 2002 
(67 FR 52896). That action proposed to require inspecting the frame for 
the correct edge distance of the two attachment holes for the 
reinforced latch support and for a crack and repairing the frame if 
necessary.
    The Direction Generale De L'Aviation Civile (DGAC), the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on ECF Model SA-365N, SA-365N1, AS-365N2, and AS 
365 N3 helicopters incorporating MOD 0753B31. The DGAC advises of the 
discovery of a crack on the left-hand side of the frame.
    ECF has issued AS 365 Alert Service Bulletin No. 53.00.42, dated 
January 31, 2001 (ASB). The ASB specifies measuring the edge distance 
of the attachment holes for the reinforced latch support of the frame, 
inspecting for a crack, installing a repair on the frame or stop-
drilling the crack, and monitoring the crack for continued growth. The 
DGAC classified this ASB as mandatory and issued AD No. 2001-060-
052(A), dated February 21, 2001, to ensure the continued airworthiness 
of these helicopters in France.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed except for minor editorial changes. 
These changes will neither increase the economic burden on operators 
nor increase the scope of the AD.
    The FAA estimates that this AD will:
    [sbull] Affect 45 helicopters of U.S. registry,
    [sbull] Require 3 work hours per helicopter to visually inspect all 
helicopters,
    [sbull] Require 8 work hours to repair an estimated 10 helicopters 
to correct edge distance only, and
    [sbull] Require 12 work hours to repair edge distance and cracks 
for approximately five helicopters.
The average labor rate is $60 per work hour. Required parts will cost 
approximately $200, assuming a repair is necessary for 15 helicopters. 
Based on these figures, the total cost impact of the AD on U.S. 
operators is estimated to be $19,500.
    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.

[[Page 71098]]

    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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:

    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:

2002-23-04 Eurocopter France: Amendment 39-12948. Docket No. 2001-
SW-34-AD.

    Applicability: Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 
helicopters, with MOD 0753B31 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 
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 (b) 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 prevent failure of the 9-degree frame (frame) due to a crack 
at the latch support, loss of a passenger door, damage to the rotor 
system, and subsequent loss of control of the helicopter, accomplish 
the following:
    (a) Within 50 hours time-in-service, inspect each frame by 
measuring the edge distance at the two 5.2 mm (0.205 inch) diameter 
attachment holes for the latch support for the passenger door in 
accordance with the Accomplishment Instructions, paragraph 2.B.1., 
of Eurocopter France AS 365 Alert Service Bulletin 53.00.42, dated 
January 31, 2001 (ASB). Inspect the area around the attachment holes 
for a crack.
    (1) If the edge distance of both attachment holes is equal to or 
more than 8 mm (0.315 inch) and no crack is present, no action is 
required by this AD.
    (2) If the edge distance is less than 8 mm and no crack is 
present, before further flight, install a reinforcing plate in 
accordance with the Accomplishment Instructions paragraph 2.B.2. of 
the ASB. Accomplishing the requirements of paragraph 2.B.2. of the 
ASB constitutes terminating action for the requirements of this AD.
    (3) If there is a crack, before further flight, stop-drill the 
crack with a 3-millimeter diameter hole and repair the frame in 
accordance with the Accomplishment Instructions, paragraph 2.B.3., 
of the ASB. Accomplishing the requirements of paragraph 2.B.3. of 
the ASB constitutes terminating action for the requirements of this 
AD.
    (b) 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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (c) Special flight permits may be issued in accordance with 14 
CFR 21.197 and 21.199 to operate the helicopter to a location where 
the requirements of this AD can be accomplished.
    (d) The inspection and repair shall be done in accordance with 
the Accomplishment Instructions of Eurocopter France AS 365 Alert 
Service Bulletin 53.00.42, dated January 31, 2001. 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.
    (e) This amendment becomes effective on January 3, 2003.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD No. 2001-060-052(A), dated 
February 21, 2001.


    Issued in Fort Worth, Texas, on November 6, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-29155 Filed 11-27-02; 8:45 am]
BILLING CODE 4910-13-P

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