[Federal Register Volume 68, Number 153 (Friday, August 8, 2003)]
[Rules and Regulations]
[Pages 47208-47211]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-19836]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-ANE-08-AD; Amendment 39-13256; AD 2003-16-03]
RIN 2120-AA64


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) that applies to Turbomeca Arriel 1A, 1 A1, 1 A2, 1 B, 1 C, 1 C1, 1 
C2, 1 D, and 1 D1 turboshaft engines. That AD currently requires 
repetitive checks for engine rubbing noise during gas generator rundown 
following engine shutdown, and for free rotation of the gas generator 
by rotating the compressor manually after the last flight of the day. 
In addition, the AD 95-11-01 requires installation of modification TU 
202 or TU 197 as terminating action to the repetitive checks. This 
amendment adds additional engine models to the applicability section, 
eliminates the installation of modification TU 197 as a terminating 
action to the repetitive checks, requires additional inspections for 
engines that have modification TU 197 installed, and requires the 
replacement of modifications TU 76 and TU 197 with modification TU 202, 
as a terminating action to the repetitive checks and inspections. This 
amendment is prompted by a report of an in-flight engine shutdown on an 
engine that had modification TU 197 installed, and the need to update 
the modification standard on certain engine models. We are issuing this 
AD to prevent engine failure due to rubbing of the 2nd stage turbine 
disk on the 2nd stage turbine nozzle guide vanes, which could result in 
complete engine failure and damage to the helicopter.

DATES: Effective September 12, 2003. The incorporation by reference of 
certain publications listed in the

[[Page 47209]]

regulations is approved by the Director of the Federal Register as of 
September 12, 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) by superseding AD 95-11-01, 
Amendment 39-9235 (60 FR 27023, May 22, 1995), which is applicable to 
Turbomeca Arriel 1A, 1 A1, 1 A2, 1 B, 1 C, 1 C1, 1 C2, 1 D, and 1 D1 
turboshaft engines was published in the Federal Register on March 10, 
2003 (68 FR 11342). That action proposed to add additional engine 
models to the applicability section, to eliminate the installation of 
modification TU 197 as a terminating action to the repetitive checks, 
to require additional inspections for engines that have modification TU 
197 installed, and to require the replacement of modifications TU 76 
and TU 197 with modification TU 202, as a terminating action to the 
repetitive checks and inspections in accordance with Turbomeca Alert 
Service Bulletin (ASB) No. A292 72 0150, Update 6, dated September 4, 
2000, and Turbomeca ASB No. A292 72 0212, Update 5, dated August 8, 
2001. Information that describes procedures for checking for unusual 
noise during gas generator rundown on engine shutdown and after the 
last flight of the day may be found in SB No. 292 72 0181, Update 3, 
dated September 15, 1995.

Addition of Helicopter Model to the Applicability

    Since the publication of the NPRM supercedure, 68 FR 11342, dated 
March 10, 2003, we have learned that these turboshaft engines are also 
installed on certain Sikorsky S-76 A helicopters. The Sikorsky S-76 A 
has also been added to the applicability.

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. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.

Correction in Note 1 to Alternative Methods of Compliance Paragraph 
Reference

    The reference in Note 1 to the alternative methods of compliance 
paragraph in the regulatory language section is corrected from (k) to 
(j) in this AD.

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 removing Amendment 39-9235 (60 FR 27023, 
May 22, 1995) and by adding a new airworthiness directive, Amendment 
39-13256, to read as follows:

2003-16-03 Turbomeca: Amendment 39-13256. Docket No. 94-ANE-08-AD. 
Supersedes AD 95-11-01, Amendment 39-9235

    Applicability: This airworthiness directive (AD) applies to 
Turbomeca turboshaft engine models Arriel 1 A, 1 A1, 1 A2, 1 B, 1 C, 
1 C2, 1 D, 1 D1, 1 E2, 1 K, 1 K1, 1 S, and 1 S1 that have not 
incorporated modification TU 202. These engines are installed on but 
not limited to Eurocopter AS-350 B, B1, and B2; SA-365 C, C2, N, N1, 
and N2; MBB-BK 117 C-1 and C-2, certain Sikorsky S-76 A, certain 
Sikorsky S-76 C, and Agusta A109 K2 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 owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (j) 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: You are responsible for having the actions required 
by this AD performed within the compliance times specified unless 
the actions have already been done.
    To prevent engine failure due to rubbing of the 2nd stage 
turbine disk on the 2nd stage nozzle guide vanes, which could result 
in complete engine failure and damage to the helicopter, do the 
following:
    (a) For Turbomeca Arriel 1 A, 1 A1, 1 A2, 1 B, 1 C, 1 C1, 1 C2, 
1 D, 1 D1, 1 E2, 1 K, 1 K1, 1 S, and 1 S1 turboshaft engines that 
have incorporated modification TU 202, no further action is 
required.
    (b) For Turbomeca Arriel turboshaft engines Models 1 B, 1 D, or 
1 D1 that have modification TU 76 or TU 197 installed, before 
further flight after the effective date of this AD, replace 
modification TU 76 or TU 197 with modification TU 202 in accordance 
with 2.B.(1) through 2.C.(2) of Arriel 1 Alert Service Bulletin 
(ASB) No. A292 72 0150, Update 6, dated September 4, 2000.

Daily Inspection for Engine Rubbing and Free Rotation

    (c) For Arriel 1 A, 1 A1, 1 A2, 1 C, 1 C1, 1 C2, 1 E2, 1 K, 1 
K1, 1 S, and 1 S1 engines with modification TU 197 installed, 
perform the following daily checks:
    (1) After the last flight of the day or after a ventilation 
(maximum of 5 seconds), immediately after engine stopping, listen 
for unusual engine rubbing noise during the gas generator rundown, 
and

[[Page 47210]]

    (2) During the check after the last flight of the day, when the 
T4 temperature is below 150[deg]C (302[deg]F), perform a ventilation 
(5 seconds maximum) during gas generator rundown or check for free 
rotation of the gas generator and unusual noise by turning the 
compressor by hand.
    (3) If any rubbing noise is heard and the source of the noise 
cannot be identified, replace module M03.

Initial Borescope Inspection

    (d) For Arriel 1 A, 1 A1, 1 A2, 1 C, 1 C1, 1 C2, 1 E2, 1 K, 1 
K1, 1 S, and 1 S1 engines with modification TU 197 installed, do the 
following:
    (1) Perform initial borescope inspections for cracks of the 
second stage nozzle guide vanes (NGV2) in accordance with 2.B.(a) 
through 2.B.(c)(2) of Turbomeca ASB No. A292 72 0212, Update 5, 
dated August 8, 2001, and the schedules specified in the following 
Table 1:

                 Table 1.--Initial Borescope Inspection
------------------------------------------------------------------------
  Number of cycles-since-new or overhaul
  (CSN) on the effective date of this AD.        Initial inspection
------------------------------------------------------------------------
(1) Modules M03 with fewer than 1,000 CSN.  Before accumulating 1,100
                                             CSN.
(2) Modules M03 with 1,000 CSN or greater.  Within 100 additional cycles-
                                             in-service (CIS) after the
                                             effective date of this AD.
------------------------------------------------------------------------

    (2) If the 2nd stage nozzle guide vanes do not meet the 
acceptance criteria specified in 2.B.(c)(2) of ASB A292 72 0212, 
Update 5, dated August 8, 2001, replace module M03.

First Repetitive Borescope Inspection

    (e) Thereafter, for Arriel 1 A, 1 A1, 1 A2, 1 C, 1 C1, 1 C2, 1 
E2, 1 K, 1 K1, 1 S, and 1 S1 engines with modification TU 197 
installed, do the following:
    (1) Perform the first repetitive borescope inspection for cracks 
of the NGV2 in accordance with 2.B.(a) through 2.(c)(2) of Turbomeca 
ASB No. A292 72 0212, Revision 5, dated August 8, 2001 and the 
schedules specified in the following Table 2:

               Table 2.--Repetitive Borescope Inspections
------------------------------------------------------------------------
  If Module M03 has already been checked       Then repeat inspection
------------------------------------------------------------------------
(1) Once, before 900 CSN..................  Before 1,100 CSN and then
                                             between 1,900 and 2,100
                                             CSN.
(2) Twice, before 900 CSN without           Before 1,500 CSN.
 propagation of cracks recorded between
 the first and second check.
(3) Twice, before 900 CSN with propagation  Before 1,100 CSN and then
 of cracks recorded between the first and    between 1,900 and 2,100
 second check.                               CSN.
(4) Once, after 900 CSN...................  Between 1,900 and 2,100 CSN.
------------------------------------------------------------------------

    (2) If the 2nd stage nozzle guide vanes do not meet the 
acceptance criteria specified in 2.B.(c)(2) of ASB A292 72 0212, 
Update 5, dated August 8, 2001, replace module M03.

Subsequent Repetitive Borescope Inspection

    (f) Thereafter, for Arriel 1 A, 1 A1, 1 A2, 1 C, 1 C1, 1 C2, 1 
E2, 1 K, 1 K1, 1 S, and 1 S1 engines with modification TU 197 
installed, do the following:
    (1) Repeat the borescope inspection of the NGV2 in accordance 
with 2.B.(a) through 2.B.(c)(2) of Turbomeca ASB No. A292 72 0212, 
Update 5, dated August 8, 2001 at intervals not to exceed 2,100 
cycles-since-last-inspection (CSLI).
    (2) If the 2nd stage nozzle guide vanes do not meet the 
acceptance criteria specified in 2.B.(c)(2) of ASB A292 72 0212, 
Update 5, dated August 8, 2001, replace module M03.

Replacement of Modification TU 197

    (g) For 1 A, 1 A1, 1 A2, 1 C, 1 C1, 1 C2, 1 E2, 1K, 1 K1, 1 S, 
and 1 S1 engines that have modification TU 197 installed, install 
the improved 2nd stage nozzle guide vanes, modification TU 202 at 
next shop visit after the effective date of this AD, but not later 
than December 31, 2006, in accordance with 2.B. through 2.C. of 
Arriel 1 ASB No. A292 72 0150, Update No. 6, dated September 4, 
2000.

Terminating Action

    (h) Installation of the improved 2nd stage nozzle guide vane, 
modification TU202, constitutes terminating action to the checks and 
inspections required by paragraphs (c)(1), (c)(2), and (d)(1) 
through (d)(3) of this AD.
    (i) The checks required by paragraph (c)(1) and (c)(2) of this 
AD may be performed by the pilot holding at least a private pilot 
certificate as an exception to the requirements of part 43 of the 
Federal Aviation Regulations (14 CFR part 43). The checks must be 
recorded in accordance with Sec. Sec.  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.

Alternative Methods of Compliance

    (j) 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 2: 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

    (k) 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 helicopter to a location where 
the requirements of this AD can be done.

Documents That Have Been Incorporated by Reference

    (l) The actions must be done in accordance with the following 
Turbomeca alert service bulletins:

 
----------------------------------------------------------------------------------------------------------------
              Document No.                         Pages             Revision                 Date
----------------------------------------------------------------------------------------------------------------
A292 72 0150...........................  All.....................            6  September 4, 2000.
    Total pages: 9
A292 72 0212...........................  All.....................            5  August 8, 2001.
    Total pages: 12
----------------------------------------------------------------------------------------------------------------

    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 3: The subject of this AD is addressed in DGAC 
airworthiness directive DGAC 98-311 (A) R1, dated October 7, 1998.

Effective Date

    (m) This amendment becomes effective on September 12, 2003.


[[Page 47211]]


    Issued in Burlington, Massachusetts, on July 29, 2003.
Robert G. Mann,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-19836 Filed 8-7-03; 8:45 am]
BILLING CODE 4910-13-P