[Federal Register Volume 63, Number 110 (Tuesday, June 9, 1998)]
[Rules and Regulations]
[Pages 31347-31348]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-15124]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-07-AD; Amendment 39-10571; AD 98-12-15]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS 332C, L, L1,
and L2 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 AS 332C, L, L1, and L2
helicopters that requires visually inspecting the intermediate gearbox-
to-structure attachment stirrup (stirrup) front tabs for cracks, and if
a crack is discovered, removing the intermediate gearbox and replacing
it with an airworthy intermediate gearbox; and inspecting for the
conformity of the attachment parts. This amendment is prompted by five
reports of failure of the two stirrup tabs. The actions specified by
this AD are intended to prevent failure of the intermediate gearbox
stirrup front tabs, loss of anti-torque drive, 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. Scott Horn, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5125, 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 AS 332C,
L, L1, and L2 helicopters was published in the Federal Register on
April 7, 1998 (63 FR 16916). That action proposed to require visually
inspecting the stirrup front tabs for cracks, and if a crack is
discovered, removing the intermediate gearbox and replacing it with an
airworthy intermediate gearbox; and inspecting for the conformity of
the attachment parts.
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 an editorial change in the
``Applicability'' section of the AD where the word ``and'' has been
changed to ``or.'' This change is to make it clear that this AD applies
to the affected model helicopters when either of the three part numbers
is installed. The FAA has determined that this change will neither
increase the economic burden on an operator nor increase the scope of
the AD.
The FAA estimates that 4 helicopters of U.S. registry will be
affected by this AD, that it will take approximately 0.25 work hours to
inspect the tabs, and 3 work hours to inspect for conformity, and that
the average labor rate is $60 per work hour. Based on these figures,
the total cost impact of the AD on U.S. operators is estimated to be
$780.
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
[[Page 31348]]
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 98-12-15 Eurocopter France: Amendment 39-10571. Docket No. 98-
SW-07-AD.
Applicability: Model AS 332C, L, L1, and L2 helicopters, with
intermediate gearboxes (IGB), part numbers (P/N) 332A35-0002 all
dash numbers, 332A35-0010 all dash numbers, or 332A35-0011-01,
installed, except those IGBs modified in accordance with MOD 0761049
or MOD 0761050, 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 (c) 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 failure of the IGB-to-structure attachment stirrup
(stirrup) front tabs, loss of anti-torque drive, and subsequent loss
of control of the helicopter, accomplish the following:
(a) Before the first flight of each day, perform a visual
inspection of the stirrup front tabs for cracks in accordance with
paragraph 2.B.1) of the Accomplishment Instructions in Eurocopter
France AS 332 Service Bulletin 01.00.47, Revision No. 1, dated
September 10, 1997 (SB). If a crack is found, remove the IGB and
replace it with an airworthy IGB before further flight. Completion
of the conformity procedure contained in paragraph 2.B.2.1.3) of the
SB is terminating action for the requirement of this AD to inspect
for cracks prior to the first flight of each day.
(b) Within 100 hours time-in-service (TIS), inspect the two
front attaching assemblies securing the stirrup of the IGB to the
angle bracket of the structure (attachment assembly) for thickness
of the stirrup front tabs in accordance with paragraph 2.B.2) of the
SB.
(1) If the attachment assembly meets the conformity requirements
of either paragraph 2.B.2.1.1) or 2.B.2.1.2) of the SB, reassemble
the attachment assembly in accordance with paragraph 2.B.2.1.3) of
the SB.
(2) If the attachment assembly does not meet the conformity
requirements of either paragraph 2.B.2.1.1) or 2.B.2.1.2) of the SB,
replace it with an attachment assembly which does meet the
conformity requirements of either of those paragraphs. Install the
attachment assembly hardware in accordance with 2.B.2.1.3) of the
SB.
(3) If a crack is discovered in the stirrup front tabs as a
result of the conformity inspection, remove the IGB and replace it
with an airworthy IGB before further flight.
(c) 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, FAA, Rotorcraft Directorate,
Rotorcraft Standards Staff. 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.
(d) 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.
(e) The inspections and replacement, if necessary, shall be done
in accordance with Eurocopter France AS 332 Service Bulletin
01.00.47, Revision No. 1, dated September 10, 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.
(f) 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 96-263-060(AB)R1 for
Eurocopter France (ECF) Model AS 332C, L, and L1 helicopters, and AD
96-262-004(AB)R1 for ECF Model AS 332L2 helicopters, both dated
November 5, 1997.
Issued in Fort Worth, Texas, on May 29, 1998.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-15124 Filed 6-8-98; 8:45 am]
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