Airworthiness Directives; Eurocopter France Model SE 3130, SA 3180, SE 313B, SA 318B, and SA 318C Helicopters

[Federal Register Volume 65, Number 31 (Tuesday, February 15, 2000)]
[Rules and Regulations]
[Pages 7427-7428]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-3223]



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Federal Register / Vol. 65, No. 31 / Tuesday, February 15, 2000 / 
Rules and Regulations

[[Page 7427]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-65-AD; Amendment 39-11563; AD 2000-03-06]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SE 3130, SA 
3180, SE 313B, SA 318B, and SA 318C Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to Eurocopter France Model SE 3130, SA 3180, SE 313B, 
SA 318B, and SA 318C helicopters, that currently requires visual 
inspections and modification, if necessary, of the horizontal 
stabilizer spar tube (spar tube). This amendment requires the same 
actions required by the existing AD, visually inspecting the four half-
shell attachment clamps for cracks, and fitting a safety wire around 
the attachment clamps. 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 of the horizontal stabilizer and impact with 
the main or tail rotor, and subsequent loss of control of the 
helicopter.

DATES: Effective March 21, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 21, 2000.

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: 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) by superseding AD 98-12-20, 
Amendment 39-10574 (63 FR 31350, June 9, 1998), which is applicable to 
Eurocopter France Model SE 3130, SA 3180, SE 313B, SA 318B, and SA 318C 
helicopters, was published in the Federal Register on November 18, 1999 
(64 FR 62988). That action proposed to require visually inspecting and 
modifying, if necessary, the spar tube, visually inspecting the four 
half-shell attachment clamps for cracks, and fitting a safety wire 
around the attachment clamps.
    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 will be 
affected by this AD. It will take approximately 0.5 work hour per 
helicopter to accomplish the inspection, 3 work hours per helicopter to 
accomplish the modification, and 1 work hour per helicopter to 
accomplish the attachment clamp inspection and install the safety wire. 
Required parts will cost approximately $1,100 per helicopter. Based on 
these figures, the total cost impact of the AD on U.S. operators is 
estimated to be $19,180.
    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.
    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 removing Amendment 39-10574 (63 FR 
31350, June 9, 1998), and by adding a new airworthiness directive (AD), 
Amendment 39-11563, to read as follows:

AD 2000-03-06  Eurocopter France: Amendment 39-11563. Docket No. 98-
SW-65-AD. Supersedes AD 98-12-20, Amendment 39-10574, Docket No. 98-
SW-03-AD.

    Applicability: Model SE 3130, SA 3180, SE 313B, SA 318B, and SA 
318C 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 
otherwise modified, altered, or repaired in the area subject to the 
requirements of this

[[Page 7428]]

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 (g) 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 fatigue failure of the horizontal stabilizer spar 
tube (spar tube), separation of the horizontal stabilizer and impact 
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 
to determine whether Modification 072214 (installing the spar tube 
without play) or Modification 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 SA3130/3180 Service 
Bulletin No. 55.10, Revision 3, dated May 4, 1998 (SB). 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 SB.

    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 SB. 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 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 SB.
    (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 SB.
    (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, 3,200 hours total 
TIS, or 144 calendar months 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 SB.
    (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 SB.
    (f) Within 30 calendar days, visually inspect the four 
attachment clamps of the half-shells and install a safety wire 
around the four attachment clamps in accordance with paragraph 
2.B.2)d) of the SB. If any attachment clamp is found cracked, 
replace it with an airworthy attachment clamp and install a safety 
wire around the replacement attachment clamp before further flight.
    (g) 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.

    (h) 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.
    (i) The inspections and modifications shall be done in 
accordance with paragraphs 2.A, 2.B.1), 2.B.1)b), 2.B.2)a), 
2.B.2)b), 2.B.2)c), 2.B.2)d), and 2.B.3) of the Accomplishment 
Instructions of Eurocopter France SA3130/3180 Service Bulletin No. 
55.10, Revision 3, dated May 4, 1998. 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.
    (j) This amendment becomes effective on March 21, 2000.

    Note 4: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 96-278-054(A)R2, dated 
July 29, 1998.


    Issued in Fort Worth, Texas, on February 7, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-3223 Filed 2-14-00; 8:45 am]
BILLING CODE 4910-13-U

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