[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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