[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