[Federal Register Volume 59, Number 240 (Thursday, December 15, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-30180]
[[Page Unknown]]
[Federal Register: December 15, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 93-ANE-78; Amendment 39-9092; AD 94-25-08]
Airworthiness Directives; Turbomeca Arriel 1 Series Turboshaft
Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to Turbomeca Arriel 1 series turboshaft engines, that
currently requires a gearbox chip detector inspection prior to further
flight, subsequent inspection at designated intervals, and if
necessary, removal of the gearbox, and also requires modification of
the gearbox if not accomplished previously. This amendment requires
modification to the intermediate gear that would constitute terminating
action to the repetitive chip detector inspections. On certain engines
this amendment requires immediate modification of the intermediate gear
prior to further flight. This amendment is prompted by the availability
of design improvements to the intermediate gear. The actions specified
by this AD are intended to prevent damage to the aircraft resulting
from engine debris following an uncontained engine failure.
DATES: Effective January 17, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 17, 1995.
ADDRESSES: The service information referenced in this AD may be
obtained from Turbomeca Engine Corporation, 2709 Forum Drive, Grand
Prairie, TX 75051. This information may be examined at the Federal
Aviation Administration (FAA), New England Region, Office of the
Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA
01803-5299; or at the Office of the Federal Register, 800 North Capitol
Street NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Mark A. Rumizen, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (617)
238-7137, fax (617) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding airworthiness
directive (AD) 92-24-08, Amendment 39-8413 (57 FR 54293, November 18,
1992), which is applicable to Turbomeca Arriel 1B, 1D, 1D1, 1A with
TU13, and 1A1 with TU13, turboshaft engines, was published in the
Federal Register on March 15, 1994 (59 FR 11944). That action proposed
to require removing gearboxes that were overhauled prior to June 1,
1992, within 30 days after the effective date of that AD. Those
gearboxes have intermediate gears that are prone to gear teeth wear due
to mixing of used gear train components with new components. That
proposed AD would also require immediate modification of certain
engines to the TU39 which introduces a thicker web intermediate gear
that is more resistant to high cycle fatigue (HCF) failure. Finally,
that proposed AD would also continue to require repetitive inspections
of the chip detector for evidence of metal chips until installation of
modification TU232 to the intermediate gear at the next overhaul or
repair of the reduction gearbox. Installation of modification TU232
would constitute terminating action to the inspection requirements of
that AD. The actions would be required to be accomplished in accordance
with Turbomeca Service Bulletin (SB) No. 292 72 0157, Update No. 2,
dated July 30, 1993, and Turbomeca SB No. 292 72 0169, dated July 12,
1993.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
One commenter (the manufacturer) states that the economic analysis
in the proposed rule is incorrect, and provides revised economic
information. The FAA concurs and has revised the economic analysis of
this final rule accordingly.
One commenter states that the provision to allow the pilot to
perform the chip detector inspection that was specified in AD 92-24-08
should be included in this AD. The FAA concurs and the compliance
section has been revised to include this provision.
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes described
previously. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
The FAA estimates that 270 engines installed on aircraft of U.S.
registry will be affected by this AD, that it will take approximately 4
work hours per engine to accomplish the required actions, and that the
average labor rate is $55 per work hour. Required parts will cost
approximately $4,222 per engine. Based on these figures, the total cost
impact of the AD on U.S. operators is estimated to be $1,199,340.
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment Section 39.13 is
amended by removing amendment 39-8413 (57 FR 54293, November 18, 1992)
and by adding a new airworthiness directive, Amendment 39-9092, to read
as follows:
94-25-08 Turbomeca: Amendment 39-9092. Docket 93-ANE-78. Supersedes
AD 92-24-08, Amendment 39-8413.
Applicability: Turbomeca Arriel Model 1B, 1D, 1D1, 1A with TU13,
and 1A1 with TU13, turboshaft engines installed on but not limited
to Aerospatiale AS-350B helicopters.
Compliance: Required as indicated, unless accomplished
previously.
To prevent damage to the aircraft resulting from engine debris
following an uncontained engine failure, accomplish the following:
(a) For the following Turbomeca Arriel engine models: 1D not
modified to TU232, 1D1 not modified to TU232, 1B modified to TU39
but not modified to TU232, 1A with TU13 modified to TU39 but not
modified to TU232, and 1A1 with TU13 modified to TU39 but not
modified to TU232, accomplish the following:
(1) Except for those engines that have been inspected in
accordance with AD 92-24-08 within 8 hours time in service (TIS)
prior to the effective date of this AD, prior to further flight
remove and inspect the reduction gearbox chip detector for evidence
of metal chips.
(2) Remove from service reduction gearbox modules that do not
meet the return to service criteria described in Turbomeca SB No.
292 72 0157, Update No. 2, dated July 30, 1993, and replace with a
serviceable part.
(3) Thereafter, at intervals not to exceed 8 hours TIS since the
last inspection, accomplish the following:
(i) Remove and inspect the reduction gearbox chip detector in
accordance with paragraph (a)(1) of this AD.
(ii) Remove from service, if necessary, the reduction gearbox
module in accordance with paragraph (a)(2) of this AD, and replace
with a serviceable part.
(4) At the next overhaul or repair of the reduction gearbox
module after the effective date of this AD, incorporate modification
TU232 in accordance with Turbomeca SB No. 292 72 0169, dated July
12, 1993. Incorporation of modification TU232 constitutes
terminating action to the inspections, and replacement, if
necessary, required in paragraphs (a)(1), (a)(2), and (a)(3) of this
AD.
(b) For the following Turbomeca Arriel engine models: 1B not
modified to TU39, 1A with TU13 not modified to TU39, and 1A1 with
TU13 not modified to TU39, prior to further flight replace reduction
gearbox module No. 5 with a reduction gearbox module No. 5 modified
to standard TU39.
(c) For the following Turbomeca Arriel engine models: 1B, 1A
with TU13, and 1A1 with TU13; with reduction gearbox modules
identified by serial numbers specified in paragraph C.(c) of
Turbomeca SB No. 292 72 0157, Update No. 2, dated July 30, 1993,
that were overhauled prior to June 1, 1992, but not overhauled
between that date and the effective date of this AD, and with less
than 200 hours TIS since overhaul, remove from service and return
for overhaul within 30 days after the effective date of this AD, in
accordance with Turbomeca Service Bulletin (SB) No. 292 72 0157,
Update No. 2, dated July 30, 1993.
(d) The checks required by paragraphs (a)(1) and (a)(3)(i) of
this AD may be performed by the pilot holding at least a private
pilot certificate as a n exception to the requirements of part 43 of
the Federal Aviation Regulations (14 CFR part 43). The checks must
be recorded in accordance with Sections 43.9 and 91.417(a)(2)(v) of
the Federal Aviation Regulations (14 CFR 43.9 and 14 CFR
91.417(a)(2)(v)), and the records must be maintained as required by
the applicable Federal Aviation Regulation.
(e) 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, Engine Certification Office. The
request should be forwarded through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Engine Certification Office.
Note: Information concerning the existence of approved
alternative method of compliance with this AD, if any, may be
obtained from the Engine Certification Office.
(f) 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 aircraft to a location where
the requirements of this AD can be accomplished.
(g) The actions required by this AD shall be done in accordance
with the following service bulletins:
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Document No. Pages Update Date
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Turbomeca SB No. 292 72 0157. 1-5 2.......... July 30, 1993.
Total pages: 5.
Turbomeca SB No. 292 72 0169. 1-5 Original... July 12, 1993.
Total pages: 5.
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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 Turbomeca Engine Corporation,
2709 Forum Drive, Grand Prairie, TX 75051. Copies may be inspected
at the FAA, New England Region, Office of the Assistant Chief
Counsel, 12 New England Executive Park, Burlington, MA; or at the
Office of the Federal Register, 800 North Capitol Street NW., suite
700, Washington, DC.
(h) This amendment becomes effective on January 17, 1995.
Issued in Burlington, Massachusetts, on December 2, 1994.
James C. Jones,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 94-30180 Filed 12-14-94; 8:45 am]
BILLING CODE 4910-13-P
