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