Airworthiness Directives; Rolls-Royce Corporation AE 2100D3 Turboprop Engines, 75108-75109 [E6-21185]

Download as PDF 75108 Federal Register / Vol. 71, No. 240 / Thursday, December 14, 2006 / Rules and Regulations Leichtflugzeugbau GmbH, Dr. Kurt Steim Strasse 6, D–78713 Schramberg. (iii) You may remove the propeller hub and return as specified in paragraph (e)(1)(ii) of this AD at any time prior to accumulating 15 hours TIS on the propeller to terminate the inspection requirement of paragraph (e)(1)(i) of this AD. (2) For propellers with 15 or more hours TIS as of the effective date of this AD: Prior to further flight, remove the propeller hub and return to the propeller manufacturer for inspection and overhaul. Send the propeller hub along with the propeller hours time-inservice (TIS) to Technoflug Leichtflugzeugbau GmbH, Dr. Kurt Steim Strasse 6, D–78713 Schramberg. (3) For all sailplanes: With the propeller removed, the powered sailplane can temporarily be used in the sailplane configuration. If the engine battery (at the steel frame between the seats) is not removed, a new weight and balance report is not necessary. After the inspection and overhaul of the propeller hub is done, the propeller must be reinstalled. FAA AD Differences mstockstill on PROD1PC61 with RULES Note: This AD differs from the MCAI and/ or service information as follows: (1) The MCAI did not have a required action if cracks were found during the inspection. This AD requires the propeller hub to be overhauled by the manufacturer before further flight if cracks are found. (2) The MCAI allowed continued flight over the 15 hour propeller TIS limit (up to the annual inspection) if the propeller TIS was less than 15 hours as of the effective date of this AD. For propellers at or less than 15 hours TIS, the FAA is requiring the propeller hub to be overhauled by the manufacturer upon the accumulation of 15 hours TIS or prior to further flight if cracks are found, whichever occurs first. (3) The service information allows for the pilot to perform the inspection and the removal and reinstallation of the propeller. By FAA regulation (14 CFR part 43), the pilot is not allowed to do these actions and an appropriately-rated mechanic must perform these actions. (4) The MCAI incorporates the service information. We have modified the procedures in the service information as stated above and incorporated the procedures into this AD. This AD only references the service information. Other FAA AD Provisions (f) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Staff, FAA, ATTN: Gregory Davison Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; fax: (816) 329–4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA- VerDate Aug<31>2005 15:47 Dec 13, 2006 Jkt 211001 approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (g) Refer to European Aviation Safety Agency (EASA) AD No.: 2006–0294–E, dated September 25, 2006, and Schempp-Hirth Flugzeugbau GmbH Technical Note No. 890– 8/868–11, dated September 22, 2006, for related information. Material Incorporated by Reference (h) None. Issued in Kansas City, Missouri on December 7, 2006. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–21212 Filed 12–13–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26414; Directorate Identifier 2006–NE–42–AD; Amendment 39– 14854; AD 2006–25–13] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Corporation AE 2100D3 Turboprop Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: The FAA is adopting a new airworthiness directive (AD) for RollsRoyce Corporation (RRC) AE 2100D3 turboprop engines. This AD requires removing certain part number (P/N) compressor cone shaft assemblies at a new reduced cyclic life limit of 5,000 engine cycles. This AD results from lowcycle-fatigue testing and analysis of certain P/N compressor cone shaft assemblies, by RRC. We are issuing this AD to prevent uncontained failure of the compressor cone shaft assembly, leading to engine shutdown and damage to the airplane. DATES: This AD becomes effective December 29, 2006. We must receive any comments on this AD by February 12, 2007. SUMMARY: PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 Use one of the following addresses to comment on this AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Governmentwide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Rolls-Royce Corporation, P.O. Box 420, Indianapolis, IN 46206–0420; telephone (317) 230–6400; fax (317) 230–4243 for the service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Michael Downs, Aerospace Engineer, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, IL 60018–4696; telephone (847) 294–7870; fax (847) 294–7834. SUPPLEMENTARY INFORMATION: RRC conducted low-cycle-fatigue testing, and strength and life analysis, of compressor cone shaft assemblies, P/Ns 23050728, 23070729, and 23076017. The study concluded that these compressor cone shaft assemblies have a lower fatigue life than originally calculated. This condition, if not corrected, could result in uncontained failure of the compressor cone shaft assembly, leading to engine shutdown and damage to the airplane. ADDRESSES: FAA’s Determination and Requirements of This AD Although no airplanes that are registered in the United States use these RRC AE 2100D3 turboprop engines, the possibility exists that the engines could be used on airplanes that are registered in the United States in the future. The unsafe condition described previously is likely to exist or develop on other AE 2100D3 turboprop engines of the same type design. We are issuing this AD to prevent uncontained failure of the compressor cone shaft assembly, leading to engine shutdown and damage to the airplane. This AD requires removing compressor cone shaft assemblies, P/Ns 23050728, 23070729, and 23076017, at a new reduced cyclic life limit of 5,000 engine cycles. The original cyclic life limit was 20,000 engine cycles. RRC will revise Chapter 5 of the maintenance E:\FR\FM\14DER1.SGM 14DER1 Federal Register / Vol. 71, No. 240 / Thursday, December 14, 2006 / Rules and Regulations manual to show the new reduced cyclic life limit of 5,000 engine cycles. FAA’s Determination of the Effective Date Since there are currently no domestic operators of this engine model, notice and opportunity for public comment before issuing this AD are unnecessary. A situation exists that allows the immediate adoption of this regulation. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to send us any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘AD Docket No. FAA–2006–26414; Directorate Identifier 2006–NE–42–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Using the search function of the DMS Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78) or you may visit https://dms.dot.gov. mstockstill on PROD1PC61 with RULES 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. 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 VerDate Aug<31>2005 15:47 Dec 13, 2006 Jkt 211001 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 the regulation: 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. 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, Safety. Adoption of the Amendment Under 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: 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] 2006–25–13 Rolls-Royce Corporation (formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison): Amendment 39– 14854. Docket No. FAA–2006–26414; Directorate Identifier 2006–NE–42–AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 29, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Rolls-Royce Corporation (RRC) AE 2100D3 turboprop engines with a compressor cone shaft assembly, part number 23050728, 23070729, or 23076017, installed. These engines are installed on, but not limited to, Lockheed Martin C–130J military transport airplanes. Unsafe Condition (d) This AD results from low-cycle-fatigue testing and analysis of the affected compressor cone shaft assemblies, by RRC. We are issuing this AD to prevent uncontained failure of the compressor cone shaft assembly, leading to engine shutdown and damage to the airplane. 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. Removal of Compressor Cone Shaft Assemblies (f) After the effective date of this AD, remove compressor cone shaft assemblies from service at the new reduced life limit of 5,000 engine cycles. Alternative Methods of Compliance (g) 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 (h) Rolls-Royce Corporation Alert Service Bulletin No. AE 2100D3–A–72–249, dated March 14, 2006, pertains to the subject of this AD. Material Incorporated by Reference (i) None. Issued in Burlington, Massachusetts, on December 6, 2006. Diane Cook, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6–21185 Filed 12–13–06; 8:45 am] BILLING CODE 4910–13–P 2. The FAA amends § 39.13 by adding the following new airworthiness directive: I PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 75109 E:\FR\FM\14DER1.SGM 14DER1

Agencies

[Federal Register Volume 71, Number 240 (Thursday, December 14, 2006)]
[Rules and Regulations]
[Pages 75108-75109]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-21185]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26414; Directorate Identifier 2006-NE-42-AD; 
Amendment 39-14854; AD 2006-25-13]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Corporation AE 2100D3 
Turboprop Engines

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

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Rolls-Royce Corporation (RRC) AE 2100D3 turboprop engines. This AD 
requires removing certain part number (P/N) compressor cone shaft 
assemblies at a new reduced cyclic life limit of 5,000 engine cycles. 
This AD results from low-cycle-fatigue testing and analysis of certain 
P/N compressor cone shaft assemblies, by RRC. We are issuing this AD to 
prevent uncontained failure of the compressor cone shaft assembly, 
leading to engine shutdown and damage to the airplane.

DATES: This AD becomes effective December 29, 2006.
    We must receive any comments on this AD by February 12, 2007.

ADDRESSES: Use one of the following addresses to comment on this AD:
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Governmentwide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Rolls-Royce Corporation, P.O. Box 420, Indianapolis, IN 
46206-0420; telephone (317) 230-6400; fax (317) 230-4243 for the 
service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Michael Downs, Aerospace Engineer, 
Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des 
Plaines, IL 60018-4696; telephone (847) 294-7870; fax (847) 294-7834.

SUPPLEMENTARY INFORMATION: RRC conducted low-cycle-fatigue testing, and 
strength and life analysis, of compressor cone shaft assemblies, P/Ns 
23050728, 23070729, and 23076017. The study concluded that these 
compressor cone shaft assemblies have a lower fatigue life than 
originally calculated. This condition, if not corrected, could result 
in uncontained failure of the compressor cone shaft assembly, leading 
to engine shutdown and damage to the airplane.

FAA's Determination and Requirements of This AD

    Although no airplanes that are registered in the United States use 
these RRC AE 2100D3 turboprop engines, the possibility exists that the 
engines could be used on airplanes that are registered in the United 
States in the future. The unsafe condition described previously is 
likely to exist or develop on other AE 2100D3 turboprop engines of the 
same type design. We are issuing this AD to prevent uncontained failure 
of the compressor cone shaft assembly, leading to engine shutdown and 
damage to the airplane. This AD requires removing compressor cone shaft 
assemblies, P/Ns 23050728, 23070729, and 23076017, at a new reduced 
cyclic life limit of 5,000 engine cycles. The original cyclic life 
limit was 20,000 engine cycles. RRC will revise Chapter 5 of the 
maintenance

[[Page 75109]]

manual to show the new reduced cyclic life limit of 5,000 engine 
cycles.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this engine 
model, notice and opportunity for public comment before issuing this AD 
are unnecessary. A situation exists that allows the immediate adoption 
of this regulation.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to send us any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. FAA-2006-26414; 
Directorate Identifier 2006-NE-42-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify it.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of the DMS Web 
site, anyone can find and read the comments in any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc.). 
You may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78) or you may visit 
https://dms.dot.gov.

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.

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 the regulation:
    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.
    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, Safety.

Adoption of the Amendment

0
Under 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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2006-25-13 Rolls-Royce Corporation (formerly Allison Engine Company, 
Allison Gas Turbine Division, and Detroit Diesel Allison): Amendment 
39-14854. Docket No. FAA-2006-26414; Directorate Identifier 2006-NE-
42-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
29, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce Corporation (RRC) AE 2100D3 
turboprop engines with a compressor cone shaft assembly, part number 
23050728, 23070729, or 23076017, installed. These engines are 
installed on, but not limited to, Lockheed Martin C-130J military 
transport airplanes.

Unsafe Condition

    (d) This AD results from low-cycle-fatigue testing and analysis 
of the affected compressor cone shaft assemblies, by RRC. We are 
issuing this AD to prevent uncontained failure of the compressor 
cone shaft assembly, leading to engine shutdown and damage to the 
airplane.

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.

Removal of Compressor Cone Shaft Assemblies

    (f) After the effective date of this AD, remove compressor cone 
shaft assemblies from service at the new reduced life limit of 5,000 
engine cycles.

Alternative Methods of Compliance

    (g) 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

    (h) Rolls-Royce Corporation Alert Service Bulletin No. AE 
2100D3-A-72-249, dated March 14, 2006, pertains to the subject of 
this AD.

Material Incorporated by Reference

    (i) None.

    Issued in Burlington, Massachusetts, on December 6, 2006.
Diane Cook,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E6-21185 Filed 12-13-06; 8:45 am]
BILLING CODE 4910-13-P