[Federal Register Volume 63, Number 110 (Tuesday, June 9, 1998)]
[Rules and Regulations]
[Pages 31348-31350]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-15199]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-SW-07-AD; Amendment 39-10572; AD 98-12-16]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model SA 330F, G, and
J 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 SA 330F, G, and J helicopters
that requires visually inspecting the intermediate gearbox (IGB)
fairing safety stop (safety stop) for cracks, crazing, or edge wear,
and if a crack, crazing, or edge wear exceeds the established limits,
replacing the safety stop; and, inspecting to ensure that the inclined
drive shaft fairing hinge pin is properly locked. A terminating action
is provided in the AD by installing an additional safety stop on the
IGB fairing. This amendment is prompted by one report of an accident
involving the loss of the inclined drive shaft fairing. The actions
specified by this AD are intended to prevent loss of the inclined drive
shaft fairing, impact with the 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
[[Page 31349]]
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. Mike Mathias, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5123, 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 SA 330F,
G, and J helicopters was published in the Federal Register on January
22, 1998 (63 FR 3273). That action proposed to require visually
inspecting the IGB safety stop for cracks, crazing, or edge wear, and
if a crack, crazing, or edge wear exceeds the established limits,
replacing the safety stop; and, inspecting to ensure that the inclined
drive shaft fairing hinge pin is properly locked. A terminating action
was provided in the AD by installing an additional safety stop on the
IGB fairing.
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 1 helicopter of U.S. registry will be
affected by this AD, that it will take approximately 1 work hour to
perform the inspection and two work hours to install the safety stop,
and that the average labor rate is $60 per work hour. Required parts
will cost approximately $50 per helicopter. Based on these figures, the
total cost impact of the AD on U.S. operators is estimated to be $230.
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 98-12-16 Eurocopter France: Amendment 39-10572. Docket No. 97-
SW-07-AD.
Applicability: Model SA 330 F, G, and J helicopters,
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 (d) 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 loss of the inclined drive shaft fairing hinge pin
(hinge pin), that could result in loss of the inclined drive shaft
fairing, impact with the tail rotor, and subsequent loss of control
of the helicopter, accomplish the following:
(a) Within 7 calendar days after the effective date of this AD,
and thereafter, upon the completion of the last flight of each day,
visually inspect the intermediate gearbox (IGB) fairing safety stop
(safety stop) and the hinge pin in accordance with the
Accomplishment Instructions of Eurocopter France SA 330 Service
Bulletin No. 54.20, Revision 1, dated February 27, 1996.
(1) Inspect the IGB fairing safety stop, part number (P/N)
330A24-2086-20, for cracks, crazing, and edge wear that exceeds the
limits stated in Note II of the Accomplishment Instructions of
Eurocopter France SA 330 Service Bulletin No. 54.20, Revision 1,
dated February 27, 1996, and if cracks, crazing, or edge wear that
exceeds the established limits is detected, remove the safety stop
and replace it with an airworthy safety stop; and,
(2) Inspect the hinge pin to ensure it is properly locked.
(b) Within 60 calendar days after the effective date of this AD,
install an additional safety stop, P/N 330A24-2119-21, to prevent
the hinge pin from backing out of its hole in case of a locking arm
failure, in accordance with Accomplishment Instructions of
Eurocopter France SA 330 Service Bulletin No. 54.20, Revision 1,
dated February 27, 1996.
(c) Installation of an airworthy additional safety stop, P/N
330A24-2119-21, constitutes terminating action for the requirements
of this AD.
(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, Rotorcraft Standards Staff,
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, Rotorcraft Standards Staff.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Standards Staff.
(e) 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.
(f) The inspection shall be done in accordance with the
Accomplishment Instructions of Eurocopter France SA 330 Service
Bulletin No. 54.20, Revision 1, dated February 27, 1996. 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
[[Page 31350]]
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
(g) This amendment becomes effective on July 14, 1998.
Note 3: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD 96-095-076(B), dated April
24, 1996.
Issued in Fort Worth, Texas, on May 29, 1998.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-15199 Filed 6-8-98; 8:45 am]
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