[Federal Register Volume 63, Number 110 (Tuesday, June 9, 1998)]
[Rules and Regulations]
[Pages 31350-31351]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-15198]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-03-AD; Amendment 39-10574; AD 98-12-20]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SE3130, SA3180, 
SE313B, SA318B, and SA318C Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to Eurocopter France Model SE3130, SA3180, SE313B, SA318B, 
and SA318C helicopters, that requires an initial and repetitive visual 
inspections and modification, if necessary, of the horizontal 
stabilizer spar tube (spar tube). This amendment is prompted by an in-
service report of fatigue cracks that initiated from corrosion pits. 
The actions specified by this AD are intended to prevent fatigue 
failure of the spar tube, separation and impact of the horizontal 
stabilizer with the main or tail rotor, and subsequent loss of control 
of the helicopter.

DATES: Effective July 14, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 14, 1998.

ADDRESSES: The service information referenced in this AD may be 
obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand 
Prairie, Texas 75053-4005. 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. Richard Monschke, Aerospace 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5116, fax 
(817) 222-5961.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to Eurocopter France Model SE3130, 
SA3180, SE313B, SA318B, and SA318C helicopters was published in the 
Federal Register on April 21, 1998 (63 FR 19668). That action proposed 
to require an initial and repetitive visual inspections and 
modification, if necessary, of the horizontal stabilizer spar tube 
(spar tube).
    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.
    The FAA estimates that 14 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 0.5 work 
hour per helicopter to accomplish the inspection and 3 work hours per 
helicopter to accomplish the modification, and that the average labor 
rate is $60 per work hour. Required parts would cost approximately 
$1100 per helicopter. Based on these figures, the total cost impact of 
the proposed AD on U.S. operators is estimated to be $1310 per 
helicopter.
    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.
    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:

AD 98-12-20  Eurocopter France: Amendment 39-10574. Docket No. 98-
SW-03-AD.

    Applicability: SE3130, SA3180, SE313B, SA318B, and SA318C 
helicopters with horizontal stabilizer, part number (P/N) 3130-35-
60-000, 3130-35-60-000-1, 3130-35-60-000-2, 3130-35-60-000-3, 3130-
35-60-000-4 or higher dash numbers, 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 (f) 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 fatigue failure of the horizontal stabilizer spar 
tube (spar tube), impact of the horizontal stabilizer with the main 
or tail rotor and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Before further flight:
    (1) Inspect the aircraft records and the horizontal stabilizer 
installation to determine whether Modification 072214 (installation 
of the spar tube without play) or Modification

[[Page 31351]]

072215 (adding two half-shells on the spar) has been accomplished.
    (2) If Modification 072214 has not been installed, comply with 
paragraphs 2.A., 2.B.1), 2.B.2)a), and 2.B.2)b) of the 
Accomplishment Instructions of Eurocopter France Service Bulletin 
No. 55.10, Revision 2, dated April 25, 1997 (service bulletin). If 
the fit and dimensions of the components specified in paragraph 
2.B.2)a) exceed the tolerances in the applicable structural repair 
manual, replace with airworthy parts.
    (3) If Modification 072215 has not been installed, first comply 
with paragraphs 2.A., 2.B.1), and 2.B.3), and then comply with 
paragraph 2.B.2)c) of the Accomplishment Instructions of the service 
bulletin.

    Note 2: Modification kit P/N 315A-07-0221571 contains the 
necessary materials to accomplish this modification.

    (b) Before the first flight of each day:
    (1) Visually inspect the installation of the half-shells, the 
horizontal stabilizer supports, and the horizontal stabilizer for 
corrosion or cracks. Repair any corroded parts in accordance with 
the applicable maintenance manual. Replace any cracked components 
with airworthy parts before further flight.
    (2) Confirm that there is no play in the horizontal stabilizer 
supports by lightly shaking the horizontal stabilizer. If play is 
detected, comply with paragraphs 2.A. and 2.B.2)a) of the service 
bulletin. If the fit and dimensions of the components specified in 
paragraph 2.B.2)a) exceed the tolerances in the applicable 
structural repair manual, replace with airworthy parts before 
further flight.
    (c) At intervals not to exceed 400 hours time-in-service (TIS) 
or four calendar months, whichever occurs first, inspect and 
lubricate the spar tube attachment bolts.
    (d) For stabilizers, P/N 3130-35-60-000, 3130-35-60-000-1, 3130-
35-60-000-2, or 3130-35-60-000-3, within 90 calendar days and 
thereafter at intervals not to exceed 18 calendar months, visually 
inspect the inside of the horizontal spar tube in accordance with 
paragraph 2.A. and 2.B.1) of the service bulletin.
    (1) If corrosion is found inside the tube, other than in the 
half-shell area, replace the tube with an airworthy tube within the 
next 500 hours TIS or 24 calendar months, whichever occurs first.
    (2) If corrosion is found inside the tube in the half-shell 
area, apply a protective treatment as described in paragraph 
2.B.1)b) of the service bulletin.
    (e) For stabilizers, P/N 3130-35-60-000-4 or higher dash 
numbers, accomplish the following:
    (1) At or before the next major inspection, 3200 hours total 
TIS, or 12 calendar years total TIS, whichever occurs first, and 
thereafter at each major inspection, visually inspect the inside of 
the horizontal spar tube in accordance with paragraph 2.A. and 
2.B.1) of the service bulletin.
    (2) If corrosion is found inside the tube, other than in the 
half-shell area, replace the tube with an airworthy tube within the 
next 500 hours TIS or 18 calendar months, whichever occurs first. If 
corrosion is found inside the tube in the half-shell area, apply a 
protective treatment as described in paragraph 2.B.1)b) of the 
service bulletin.
    (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, FAA, 
Rotorcraft Directorate. 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 modification shall be done in accordance with Eurocopter 
France Service Bulletin No. 55.10, Revision 2, dated April 25, 1997. 
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. 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 July 14, 1998.

    Note 4: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 96-278-054(B)R1, dated May 
21, 1997.

    Issued in Fort Worth, Texas, on June 2, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-15198 Filed 6-8-98; 8:45 am]
BILLING CODE 4910-13-U