Airworthiness Directives; Turbomeca Arriel 2B Series Turboshaft Engines, 61634-61635 [E6-17326]

Download as PDF 61634 Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations and pay. Paysetting for a member of the SES is based on the individual’s performance, contribution to the agency’s performance, or both, as determined under a rigorous performance management system. Since the SES and SL/ST pay systems are both subject to a performance appraisal system established under 5 U.S.C. chapter 43 and 5 CFR part 430, subparts B and C, it is essential that, for any position to be deemed equivalent, it must be subject to an equivalent performance appose of allowing a higher annual leave accrual rate is to provide agencies with an additional tool to recruit well-qualified, experienced individuals for senior positions. We believe this additional leave benefit will assist agencies in recruiting mid-career individuals who may be hesitant to enter Federal service if they have to surrender a considerable amount of personal or vacation time without an opportunity to accrue additional paid time off in a timely manner. Finally, we have amended § 630.301(b) to remove the word ‘‘Executive’’ to allow the head of any agency to request that OPM authorize the 8-hour annual leave accrual rate for additional categories of employees. We are revising this section to be consistent with the legislation. E.O. 12866, Regulatory Review This rule has been reviewed by the Office of Management and Budget in accordance with E.O. 12866. Regulatory Flexibility Act I certify that these regulations will not have a significant economic impact on a substantial number of small entities because they will apply only to Federal agencies and employees. 106 Stat. 2722, and Pub. L. 103–337, 108 Stat. 2663; subpart D also issued under Pub. L. 103–329, 108 Stat. 2423; 630.501 and subpart F also issued under E.O. 11228, 30 FR 7739, 3 CFR, 1974 Comp., p. 163; subpart G also issued under 5 U.S.C. 6305; subpart H also issued under 5 U.S.C. 6326; subpart I also issued under 5 U.S.C. 6332, Pub. L. 100–566, 102 Stat. 2834, and Pub. L. 103–103, 107 Stat. 1022; subpart J also issued under 5 U.S.C. 6362, Pub. L. 100–566, and Pub. L. 103–103; subpart K also issued under Pub. L. 105–18, 111 Stat. 158; subpart L also issued under 5 U.S.C. 6387 and Pub. L. 103–3, 107 Stat. 23; and subpart M also issued under 5 U.S.C. 6391 and Pub. L. 102–25, 105 Stat. 92. Subpart C—Annual Leave 2. In § 630.301, paragraph (b) introductory text, is revised to read as follows: I § 630.301 Annual leave accrual and accumulation—Senior Executive Service. * * * * * (b) The head of an agency may request that OPM authorize an annual leave accrual rate of 1 full day (8 hours) for each biweekly pay period for additional categories of employees who are covered by 5 U.S.C. 6301 and who hold positions that are determined by OPM to be equivalent to positions subject to the pay systems under 5 U.S.C. 5383 or 5376. Such a request must include documentation that the affected pay system is equivalent to the SES or SL/ ST pay system because it meets all three of the following conditions: * * * * * [FR Doc. E6–17389 Filed 10–18–06; 8:45 am] BILLING CODE 6325–39–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration List of Subjects in 5 CFR 630 Government employees. 14 CFR Part 39 Office of Personnel Management. Linda M. Springer, Director. [Docket No. FAA–2005–23809; Directorate Identifier 2005–NE–52–AD; Amendment 39– 14795; AD 2006–21–10] Accordingly, the interim rule amending 5 CFR part 630, which was published at 70 FR 13343 on March 21, 2005, is adopted as final with the following changes: RIN 2120–AA64 I Examining the AD Docket Airworthiness Directives; Turbomeca Arriel 2B Series Turboshaft Engines I Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. Authority: 5 U.S.C. 6311; 630.205 also issued under Pub. L. 108–411, 118 Stat 2312; 630.301 also issued under Pub. L. 103–356, 108 Stat. 3410 and Pub. L. 108–411, 118 Stat 2312; 630.303 also issued under 5 U.S.C. 6133(a); 630.306 and 630.308 also issued under 5 U.S.C. 6304(d)(3), Pub. L. 102–484, SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Turbomeca Arriel 2B, 2B1, and 2B1A turboshaft engines. This AD requires visually inspecting the splines of the high-pressure (HP) pump drive gear shaft and coupling shaft assembly for PART 630—ABSENCE AND LEAVE PWALKER on PRODPC60 with RULES 1. The authority citation for part 630 continues to read as follows: VerDate Aug<31>2005 20:58 Oct 18, 2006 Jkt 211001 AGENCY: PO 00000 Frm 00002 Fmt 4700 wear. This AD results from reports of uncommanded in-flight shutdowns of engines. We are issuing this AD to detect wear on the splines of the HP pump drive gear shaft and coupling shaft assembly, which could interrupt the fuel flow and cause an uncommanded in-flight shutdown of the engine on a single-engine helicopter. The in-flight shutdown of the engine could result in a forced autorotation landing or accident. DATES: This AD becomes effective November 24, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of November 24, 2006. ADDRESSES: You can get the service information identified in this AD from Turbomeca, 40220 Tarnos—France; Tel (33) 05 59 74 40 00; Telex 570 042; Fax (33) 05 59 74 45 15. You may examine the AD docket on the Internet at https://dms.dot.gov or in Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7175; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to Turbomeca Arriel 2B, 2B1, and 2B1A turboshaft engines. We published the proposed AD in the Federal Register on March 9, 2006 (71 FR 12150). That action proposed to require visually inspecting the splines of the HP pump drive gear shaft and coupling shaft assembly for wear. Sfmt 4700 You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. Comments We provided the public the opportunity to participate in the development of this AD. We received no E:\FR\FM\19OCR1.SGM 19OCR1 Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations comments on the proposal or on the determination of the cost to the public. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance We estimate that this AD will affect 107 engines installed on helicopters of U.S. registry. We also estimate that it will take about 1.0 work-hours per engine to perform the actions, and that the average labor rate is $65 per workhour. There are no required parts. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $6,955. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. PWALKER on PRODPC60 with RULES Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will 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. For the reasons discussed above, I certify that this AD: (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. VerDate Aug<31>2005 20:58 Oct 18, 2006 Jkt 211001 We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: I 2006–21–10 Turbomeca: Amendment 39– 14795. Docket No. FAA–2005–23809; Directorate Identifier 2005–NE–52–AD. Effective Date (a) This airworthiness directive (AD) becomes effective November 24, 2006. Affected ADs (b) None. Unsafe Condition (d) This AD results from reports of uncommanded in-flight shutdowns of engines. We are issuing this AD to detect wear on the splines of the high-pressure (HP) pump drive gear shaft and the coupling shaft assembly, which could interrupt the fuel flow and cause an uncommanded in-flight shutdown of the engine on a single-engine helicopter. The in-flight shutdown of the engine could result in a forced autorotation landing or accident. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Initial Visual Inspection (f) Perform an initial visual inspection of the splines of the coupling assembly and the HP pump drive gear shaft for wear. Use 2.A. through 2.C.(2) of the Instructions to be Incorporated of Turbomeca Mandatory Service Bulletin (MSB) No. 292 73 2812, Update No. 2, dated June 28, 2005, as follows: Frm 00003 (1) For hydraulic mechanical units (HMUs) that have accumulated 450 or more hours time-since-new (TSN) or time-since-overhaul (TSO) on the effective date of this AD, inspect within 50 hours after the effective date of this AD. Replace the HMU if worn beyond limits. (2) For HMUs that have fewer than 450 hours TSN or TSO on the effective date of this AD, inspect after accumulating 450 hours TSN or TSO, but before accumulating 500 hours TSN or TSO. Replace the HMU if worn beyond limits. Repetitive Visual Inspections (g) Thereafter, perform a visual inspection of the splines of the coupling shaft assembly and the HP pump drive gear shaft for wear every time you remove or install the HMU. Use 2.A. through 2.C.(2) of the Instructions to be Incorporated of Turbomeca MSB No. 292 73 2812, Update No. 2, dated June 28, 2005. Replace the HMU and coupling shaft assembly if worn beyond limits. Alternative Methods of Compliance (h) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (i) DGAC airworthiness directive F–2005– 188, dated November 23, 2005, also addresses the subject of this AD. Material Incorporated by Reference Applicability (c) This AD applies to Turbomeca Arriel 2B, 2B1, and 2B1A turboshaft engines. These engines are installed on, but not limited to, Eurocopter AS350B3 and EC130B4 helicopters. PO 00000 61635 Fmt 4700 Sfmt 4700 (j) You must use Turbomeca Mandatory Service Bulletin No. 292 73 2812, Update No. 2, dated June 28, 2005, to perform the visual inspections required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Turbomeca, 40220 Tarnos—France; Tel (33) 05 59 74 40 00; Telex 570 042; Fax (33) 05 59 74 45 15, for a copy of this service information. You may review copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on October 12, 2006. Thomas A. Boudreau, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6–17326 Filed 10–18–06; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\19OCR1.SGM 19OCR1

Agencies

[Federal Register Volume 71, Number 202 (Thursday, October 19, 2006)]
[Rules and Regulations]
[Pages 61634-61635]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-17326]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23809; Directorate Identifier 2005-NE-52-AD; 
Amendment 39-14795; AD 2006-21-10]
RIN 2120-AA64


Airworthiness Directives; Turbomeca Arriel 2B Series Turboshaft 
Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Turbomeca Arriel 2B, 2B1, and 2B1A turboshaft engines. This AD requires 
visually inspecting the splines of the high-pressure (HP) pump drive 
gear shaft and coupling shaft assembly for wear. This AD results from 
reports of uncommanded in-flight shutdowns of engines. We are issuing 
this AD to detect wear on the splines of the HP pump drive gear shaft 
and coupling shaft assembly, which could interrupt the fuel flow and 
cause an uncommanded in-flight shutdown of the engine on a single-
engine helicopter. The in-flight shutdown of the engine could result in 
a forced autorotation landing or accident.

DATES: This AD becomes effective November 24, 2006. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of November 24, 2006.

ADDRESSES: You can get the service information identified in this AD 
from Turbomeca, 40220 Tarnos--France; Tel (33) 05 59 74 40 00; Telex 
570 042; Fax (33) 05 59 74 45 15.
    You may examine the AD docket on the Internet at https://dms.dot.gov 
or in Room PL-401 on the plaza level of the Nassif Building, 400 
Seventh Street, SW., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803; 
telephone (781) 238-7175; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to Turbomeca Arriel 2B, 
2B1, and 2B1A turboshaft engines. We published the proposed AD in the 
Federal Register on March 9, 2006 (71 FR 12150). That action proposed 
to require visually inspecting the splines of the HP pump drive gear 
shaft and coupling shaft assembly for wear.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the Docket Management 
Facility Docket Office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone (800) 
647-5227) is located on the plaza level of the Department of 
Transportation Nassif Building at the street address stated in 
ADDRESSES. Comments will be available in the AD docket shortly after 
the DMS receives them.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We received no

[[Page 61635]]

comments on the proposal or on the determination of the cost to the 
public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

    We estimate that this AD will affect 107 engines installed on 
helicopters of U.S. registry. We also estimate that it will take about 
1.0 work-hours per engine to perform the actions, and that the average 
labor rate is $65 per work-hour. There are no required parts. Based on 
these figures, we estimate the total cost of the AD to U.S. operators 
to be $6,955.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will 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.
    For the reasons discussed above, I certify that this AD:
    (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.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2006-21-10 Turbomeca: Amendment 39-14795. Docket No. FAA-2005-23809; 
Directorate Identifier 2005-NE-52-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
24, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Turbomeca Arriel 2B, 2B1, and 2B1A 
turboshaft engines. These engines are installed on, but not limited 
to, Eurocopter AS350B3 and EC130B4 helicopters.

Unsafe Condition

    (d) This AD results from reports of uncommanded in-flight 
shutdowns of engines. We are issuing this AD to detect wear on the 
splines of the high-pressure (HP) pump drive gear shaft and the 
coupling shaft assembly, which could interrupt the fuel flow and 
cause an uncommanded in-flight shutdown of the engine on a single-
engine helicopter. The in-flight shutdown of the engine could result 
in a forced autorotation landing or accident.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

Initial Visual Inspection

    (f) Perform an initial visual inspection of the splines of the 
coupling assembly and the HP pump drive gear shaft for wear. Use 
2.A. through 2.C.(2) of the Instructions to be Incorporated of 
Turbomeca Mandatory Service Bulletin (MSB) No. 292 73 2812, Update 
No. 2, dated June 28, 2005, as follows:
    (1) For hydraulic mechanical units (HMUs) that have accumulated 
450 or more hours time-since-new (TSN) or time-since-overhaul (TSO) 
on the effective date of this AD, inspect within 50 hours after the 
effective date of this AD. Replace the HMU if worn beyond limits.
    (2) For HMUs that have fewer than 450 hours TSN or TSO on the 
effective date of this AD, inspect after accumulating 450 hours TSN 
or TSO, but before accumulating 500 hours TSN or TSO. Replace the 
HMU if worn beyond limits.

Repetitive Visual Inspections

    (g) Thereafter, perform a visual inspection of the splines of 
the coupling shaft assembly and the HP pump drive gear shaft for 
wear every time you remove or install the HMU. Use 2.A. through 
2.C.(2) of the Instructions to be Incorporated of Turbomeca MSB No. 
292 73 2812, Update No. 2, dated June 28, 2005. Replace the HMU and 
coupling shaft assembly if worn beyond limits.

Alternative Methods of Compliance

    (h) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Related Information

    (i) DGAC airworthiness directive F-2005-188, dated November 23, 
2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (j) You must use Turbomeca Mandatory Service Bulletin No. 292 73 
2812, Update No. 2, dated June 28, 2005, to perform the visual 
inspections required by this AD. The Director of the Federal 
Register approved the incorporation by reference of this service 
bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Contact Turbomeca, 40220 Tarnos--France; Tel (33) 05 59 74 40 00; 
Telex 570 042; Fax (33) 05 59 74 45 15, for a copy of this service 
information. You may review copies at the FAA, New England Region, 
Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA; or at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: https://
www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on October 12, 2006.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E6-17326 Filed 10-18-06; 8:45 am]
BILLING CODE 4910-13-P