[Federal Register Volume 68, Number 103 (Thursday, May 29, 2003)]
[Rules and Regulations]
[Pages 31970-31971]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-13115]



[[Page 31970]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-12-AD; Amendment 39-13168; AD 2003-11-09]
RIN 2120-AA64


Airworthiness Directives; Turbomeca Turmo IV A and IV C Series 
Turboshaft Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), that 
is applicable to Turbomeca Turmo IV A and IV C series turboshaft 
engines. This amendment requires initial and repetitive borescope and 
eddy current or ultrasonic inspections of centrifugal compressor intake 
wheel blades for cracks and evidence of corrosion pitting, and, if 
found cracked or if there is evidence of corrosion pitting, replacement 
with serviceable parts. This amendment is prompted by reports of 
cracked centrifugal compressor intake wheel blades, resulting in the 
release of one or more blade fragments. The actions specified by this 
AD are intended to prevent centrifugal compressor intake wheel blade 
cracks, which can result in in-flight engine power loss or shutdown.

DATES: Effective July 3, 2003. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of July 3, 2003.

ADDRESSES: The service information referenced in this AD may be 
obtained from Turbomeca, 40220 Tarnos, France; telephone (33) 05 59 64 
40 00; fax (33) 05 59 64 60 80. This information may be examined, by 
appointment, at the Federal Aviation Administration (FAA), New England 
Region, Office of the Regional 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.

FOR FURTHER INFORMATION CONTACT: Antonio Cancelliere, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; 
telephone (781) 238-7751; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an AD that is 
applicable to Turbomeca Turmo IV A and IV C series turboshaft engines 
was published in the Federal Register on December 2, 2002 (67 FR 
71493). That action proposed to require initial and repetitive 
borescope and eddy current or ultrasonic inspections of centrifugal 
compressor intake wheel blades for cracks and evidence of corrosion 
pitting, and, if found cracked or if there is evidence of corrosion 
pitting, replacement with serviceable parts in accordance with 
Turbomeca Turmo IV service bulletin (SB) 249 72 0117, dated March 11, 
2001; and Turbomeca Turmo IV SB 249 72 0100, Update 4, dated January 
25, 2000.

Comments

    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.

Editorial Corrections

    A typographical error is being corrected in the AD relative to the 
issue date of Turbomeca Turmo IV SB 249 72 0117. The Notice of Proposed 
Rule Making (NPRM) lists the issue date as March 11, 2000. That date is 
corrected in the AD to March 11, 2001.
    A typographical error is also being corrected in the Regulatory 
requirements of the AD. Paragraph (e) is corrected to (d) and paragraph 
(f) is corrected to (e).
    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 ecomomic burden on any operator nor increase the scope of 
the AD.

Economic Analysis

    There are approximately 1,110 Turbomeca Turmo IV A and IV C series 
turboshaft engines of the affected design in the worldwide fleet. The 
FAA estimates that 11 engines installed on helicopters of U.S. registry 
will be affected by this AD, that it will take approximately 41 work 
hours per engine to perform the required inspections, including 
disassembling and assembling engines and that the average labor rate is 
$60 per work hour. A replacement centrifugal compressor assembly costs 
approximately $21,651. Based on these figures, the total cost per 
inspection to U.S. operators is estimated to be $265,221.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it would not have a substantial 
direct effect 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    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 the 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 
by contacting 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

0
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

0
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]

0
2. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2003-11-09 Turbomeca: Amendment 39-13168. Docket No. 99-NE-12-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Turbomeca Turmo IV A and IV C series turboshaft engines. These 
engines are installed on but not limited to Aerospatiale FA 330--
PUMA helicopters.

    Note 1: This AD applies to each engine 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 engines that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the

[[Page 31971]]

owner/operator must request approval for an alternative method of 
compliance in accordance with paragraph (d) of this AD. The request 
should include an assessment of the effect of the modification, 
alteration, or repair on the unsafe condition addressed by this AD; 
and, if the unsafe condition has not been eliminated, the request 
should include specific proposed actions to address it.

    Compliance: Compliance is required as indicated, unless already 
done;
    To prevent centrifugal compressor intake wheel blade cracks, 
which can result in in-flight engine power loss or shutdown, do the 
following:
    (a) For engines that have been modified to TU 197 standard, but 
have not been modified to TU 191 or TU 224 standard, do the 
following:
    (1) Remove modification TU 197 and install modification TU 224 
in accordance with Turmo IV SB 249 72 0117, dated March 11, 2001, 
within the next 50 cycles or six months after the effective date of 
the AD, whichever occurs first.
    (2) Within 1,000 flight hours (FH) after the installation of 
modification TU 224 standard, do the following:
    (i) Perform a visual inspection and an ultrasonic inspection 
(USI) in accordance with paragraph 2.B.(3) of Turbomeca Turmo IV SB 
249 72 0100, Update 4, dated January 25, 2000.
    (ii) Thereafter, perform a visual inspection and a USI at 
intervals not to exceed 1,000 FH in accordance with paragraph 
2.B.(3) of Turbomeca Turmo IV SB 249 72 0100, Update 4, dated 
January 25, 2000.
    (b) For engines that have not been modified to TU 191, TU 197, 
or TU 224 standard, do the following in accordance with Turbomeca 
Turmo IV SB 249 72 0100, Update 4, dated January 25, 2000:
    (1) For centrifugal compressor intake wheels that, on the 
effective date of this AD, have been operated for more than 250 FH 
since the last inspection of the centrifugal compressor intake wheel 
blades, do the following:
    (i) Perform an initial borescope inspection of the blades for 
evidence of corrosion within the next 50 FH, or six months after the 
effective date of this AD, whichever occurs first, in accordance 
with paragraph 2.B.(1) of the SB.
    (ii) If corrosion is found, perform an eddy current inspection 
(ECI) or USI, as applicable, of the blades for cracks within 50 FH 
after the borescope inspection performed in accordance with 
paragraph 2.B.(3) of the SB, and if necessary, replace with 
serviceable parts.
    (iii) If corrosion is not found, perform an ECI or USI, as 
applicable, of the blades for cracks within 250 FH after the 
borescope inspection performed in accordance with paragraph 
(b)(1)(i) of this AD, and if necessary, replace with serviceable 
parts.
    (iv) Thereafter, perform borescope inspections and ECIs or USIs, 
as applicable, of the blades for cracks and evidence of corrosion, 
alternating at intervals not to exceed 250 FH since the last 
inspection.
    (v) Remove from service centrifugal compressor intake wheels 
found cracked and replace with serviceable parts.
    (2) For centrifugal compressor intake wheels that, upon the 
effective date of this AD, have been operated for less than or equal 
to 250 FH since the last inspection of the blades, do the following:
    (i) Perform an initial borescope inspection of the blades for 
evidence of corrosion prior to accumulating 250 FH since the last 
inspection of the blades in accordance with paragraph 2.B.(1) of the 
SB.
    (ii) If corrosion is found, perform an ECI or USI, as 
applicable, of the blades for cracks, and, if necessary, replace 
with serviceable parts, within 50 FH after the borescope inspection 
performed in accordance with paragraph 2.B.(3) of the SB.
    (iii) If corrosion is not found, perform an ECI or USI, as 
applicable, of the blades for cracks, and, if necessary, replace 
with serviceable parts, within 250 FH after the borescope inspection 
performed in accordance with paragraph (b)(2)(i) of this AD.
    (iv) Thereafter, perform borescope inspections and ECIs or USIs, 
as applicable, of the blades for cracks and evidence of corrosion, 
alternating at intervals not to exceed 250 FH since the last 
inspection.

    Note 2: Alternating intervals means that if the last inspection 
was an ECI or a USI, the next inspection will be a borescope 
inspection. If the last inspection was a borescope inspection, the 
next 250 FH inspection will be an ECI or a USI as applicable.

    (v) Remove from service centrifugal compressor intake wheels 
found cracked and replace with serviceable parts.
    (c) For engines not modified to TU 197 but have been modified to 
TU 191 or TU 224 standard, that have been operated for more than 
1,000 flight hours since the last inspection of the blades, do the 
following in accordance with Turbomeca Turmo IV SB 249 72 0100, 
Update 4, dated January 25, 2000:
    (1) Perform an initial ECI or USI, as applicable, of the blades 
for cracks, in accordance with paragraph 2.B.(3) of the SB, within 
the next 50 FH, or 6 months after the effective date of this AD, 
whichever occurs first.
    (2) Thereafter, inspect at intervals not to exceed 1,000 FH.
    (3) Remove from service centrifugal compressor intake wheels 
found cracked, and replace with a serviceable part.

Alternative Methods of Compliance

    (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, Engine Certification Office (ECO). 
Operators must submit their request through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the ECO.

Special Flight Permits

    (e) Special flight permits may be issued in accordance with 
Sec. Sec.  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 done.

Documents That Have Been Incorporated by Reference

    (f) The inspections must be done in accordance with the 
following Turbomeca service bulletins:

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             Document No.                       Pages                   Revision                   Date
----------------------------------------------------------------------------------------------------------------
Turmo IV SB 249 72 0100..............  All....................  Update No. 4...........  January 25, 2000.
    Total pages: 12
Turmo IV SB 249 72 0117..............  All....................  Original...............  March 11, 2001.
    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, 40220 Tarnos, 
France; telephone (33) 05 59 64 40 00; fax (33) 05 59 64 60 80. 
Copies may be inspected at the FAA, New England Region, Office of 
the Regional 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.

    Note 4: The subject of this AD is addressed in Direction 
Generale de L'Aviation Civile airworthiness directive AD97-122(B), 
dated May 21, 1997.

Effective Date

    (g) This amendment becomes effective on July 3, 2003.

    Issued in Burlington, Massachusetts, on May 20, 2003.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-13115 Filed 5-28-03; 8:45 am]
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