Airworthiness Directives; Rolls-Royce Corporation (Formerly Allison Engine Company) 501-D Series Turboprop Engines, 9048-9050 [E6-2454]
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9048
Federal Register / Vol. 71, No. 35 / Wednesday, February 22, 2006 / Proposed Rules
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Airbus: Docket No. FAA–2006–23948;
Directorate Identifier 2005–NM–246–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by March 24, 2006.
Related Information
(i) French airworthiness directive F–2005–
173, dated October 26, 2005, also addresses
the subject of this AD.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A319–
111, –112, –113, –114, –115, –131, –132, and
–133 airplanes; and Model A320–111, –211,
–212, –214, –231, –232, and –233 airplanes;
certificated in any category; that have
received Airbus Modification 20024 in
production (installation of a center tank),
except airplanes on which Airbus
Modification 24373 has been accomplished.
Unsafe Condition
(d) This AD results from reports that the
low-pressure warning for the fuel pumps of
the center fuel tank has come on in flight. We
are issuing this AD to ensure that the fuel
pumps do not run while dry, which could
result in a potential ignition source inside the
center fuel tank which, in combination with
flammable fuel vapors, could result in a fuel
tank explosion and consequent loss of 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.
Modification
(f) Within 20 months after the effective
date of this AD, modify the wiring to the fuel
pump control of the center fuel tank by doing
all actions specified in the Accomplishment
Instructions of Airbus Service Bulletin A320–
28–1059, Revision 06, dated June 29, 2000.
Credit for Previous Revisions of Service
Bulletin
(g) Modifications done before the effective
date of this AD in accordance with the
service bulletins identified in Table 1 of this
AD are acceptable for compliance with the
requirements of paragraph (f) of this AD.
cprice-sewell on PROD1PC66 with PROPOSALS
TABLE 1.—PREVIOUS REVISIONS OF
SERVICE BULLETIN
Airbus service
bulletin
Revision
level
A320–28–1059
04
A320–28–1059
05
VerDate Aug<31>2005
14:42 Feb 21, 2006
Date
February 4,
1999.
March 12,
1999.
Jkt 208001
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Issued in Renton, Washington, on February
10, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–2453 Filed 2–21–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001–NE–01–AD]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Corporation (Formerly Allison Engine
Company) 501–D Series Turboprop
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) for Rolls-Royce
Corporation (formerly Allison Engine
Company) (RRC) 501–D series turboprop
engines. That AD currently requires
removal from service of certain turbine
rotor components at reduced life limits.
This proposed AD would require the
same actions but adds two new life
limits. This proposed AD results from
RRC reevaluating and revising
component life limits for 501–D22 series
turboprop engines. We are proposing
this AD to prevent uncontained turbine
rotor failure resulting in an in-flight
engine shutdown and possible damage
to the airplane.
DATES: We must receive any comments
on this proposed AD by April 24, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD:
• By mail: Federal Aviation
Administration (FAA), New England
PO 00000
Frm 00055
Fmt 4702
Sfmt 4702
Region, Office of the Regional Counsel,
Attention: Rules Docket No. 2001–NE–
01–AD, 12 New England Executive Park,
Burlington, MA 01803–5299.
• By fax: (781) 238–7055.
• By e-mail: 9–ane–
adcomment@faa.gov.
You can get the service information
identified in this proposed AD from
Rolls-Royce Corporation, P.O. Box 420,
Indianapolis, IN 46206–0420; telephone
(317) 230–6400; fax (317) 230–4243.
You may examine the AD docket at
the FAA, New England Region, Office of
the Regional Counsel, 12 New England
Executive Park, Burlington, MA.
FOR FURTHER INFORMATION CONTACT:
Michael Downs, Aerospace Engineer,
Chicago Aircraft Certification Office,
FAA, 2300 East Devon Avenue, Des
Plaines, IL 60018; telephone (847) 294–
7870; fax (847) 294–7834.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No.
2001–NE–01–AD’’ in the subject line of
your comments. If you want us to
acknowledge receipt of your mailed
comments, send us a self-addressed,
stamped postcard with the docket
number written on it; we will datestamp your postcard and mail it back to
you. We specifically invite comments
on the overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. If a person contacts us
verbally, and that contact relates to a
substantive part of this proposed AD,
we will summarize the contact and
place the summary in the docket. We
will consider all comments received by
the closing date and may amend the
proposed AD in light of those
comments.
Examining the AD Docket
You may examine the AD Docket
(including any comments and service
information), by appointment, between
8 a.m. and 4:30 p.m., Monday through
Friday, except Federal holidays. See
ADDRESSES for the location.
Discussion
On March 25, 2003, we issued AD
2003–07–02, Amendment 39–13098 (68
FR 15937, April 2, 2003). That AD
requires removing from service certain
turbine rotor components at reduced life
limits. That AD resulted from RRC
updating material properties and
recalculating component life limits.
That condition, if not corrected, could
result in uncontained turbine rotor
E:\FR\FM\22FEP1.SGM
22FEP1
Federal Register / Vol. 71, No. 35 / Wednesday, February 22, 2006 / Proposed Rules
failure resulting in an in-flight engine
shutdown and possible damage to the
airplane.
Actions Since AD 2003–07–02 Was
Issued
Since we issued AD 2003–07–02, RRC
reevaluated turbine wheel assembly and
turbine wheel spacer assembly life
limits for 501–D series turboprop
engines. RRC changed certain life limits
for the 501–D22 series turboprop
engines because of recent improvements
in how low-cycle-fatigue life is
determined. RRC similarly reduced the
life limit of 2nd-3rd-stage spacer
assemblies, part numbers (P/Ns)
23033464 and 6842683, installed on
501–D22 series turboprop engines.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other products of this same
type design. We are proposing this AD,
which would require the same actions
specified in AD 2003–07–02, but for
501–D22 series turboprop engines, it
would add a life limit of 5,200 cyclesin-service for 2nd-3rd-stage spacer
assemblies, P/Ns 23033464 and
6842683.
Costs of Compliance
We estimate that this proposed AD
would affect 684 engines installed on
aircraft of U.S. registry. The proposed
action does not impose any additional
labor costs if performed at the time of
scheduled engine overhaul. Required
parts would cost about $45,000 per
engine. Based on these figures, we
estimate the total cost of the proposed
AD to U.S. operators to be $30,780,000.
cprice-sewell on PROD1PC66 with PROPOSALS
Special Flight Permits Paragraph
Removed
Paragraph (f) of the current AD, AD
2003–07–02, contains a paragraph
pertaining to special flight permits.
Even though this proposed AD does not
contain a similar paragraph, we have
made no changes with regard to the use
of special flight permits to operate the
airplane to a repair facility to do the
work required by this proposed AD. In
July 2002, we published a new Part 39
that contains a general authority
regarding special flight permits and
airworthiness directives; see Docket No.
FAA–2004–8460, Amendment 39–9474
(69 FR 47998, July 22, 2002). Thus,
VerDate Aug<31>2005
14:42 Feb 21, 2006
Jkt 208001
when we now supersede ADs we will
not include a specific paragraph on
special flight permits unless we want to
limit the use of that general authority
granted in section 39.23.
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
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD 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.
For the reasons discussed above, I
certify that the proposed 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. Would 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 proposal and placed
it in the AD Docket. You may get a copy
of this summary by sending a request to
us at the address listed under
ADDRESSES. Include ‘‘AD Docket No.
2001–NE–01–AD’’ in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
PO 00000
Frm 00056
Fmt 4702
Sfmt 4702
9049
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
proposes to amend 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–13098 (68 FR
15937, April 2, 2003) and by adding a
new airworthiness directive to read as
follows:
Rolls-Royce Corporation: Docket No. 2001–
NE–01–AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this
airworthiness directive (AD) action by April
24, 2006.
Affected ADs
(b) This AD supersedes AD 2003–07–02,
Amendment 39–13098.
Applicability
(c) This AD applies to Rolls-Royce
Corporation (formerly Allison Engine
Company) (RRC) 501–D series turboprop
engines. These engines are installed on, but
not limited to, Lockheed 188 series and 382
series turboprop airplanes, Airbus 377SG5–F
(Super Guppy) airplanes, and Convair
Models 340 and 440 airplanes which have
RRC 501–D series turboprop engines
installed under Supplemental Type
Certificate No. SE1161EA. These latter
models are commonly referred to as Convair
580/580A or 5800 models.
(d) This AD results from RRC reevaluating
and revising component life limits for 501–
D22 series turboprop engines. We are issuing
this AD to prevent uncontained turbine rotor
failure resulting in an in-flight engine
shutdown and possible 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.
501–D13 Series Engines
(f) For 501–D13 series engines, remove
turbine wheels and spacers from service as
specified in the following Table 1:
E:\FR\FM\22FEP1.SGM
22FEP1
9050
Federal Register / Vol. 71, No. 35 / Wednesday, February 22, 2006 / Proposed Rules
TABLE 1.—501–D13 SERIES LIFE LIMITS
Part name
Part number
Life limit for wheels that have complied with
commercial overhaul information letter (COIL)
401, dated May 1978
Life limit for wheels that have not complied
with COIL 401, dated May 1978
(1) Second-stage turbine wheel assembly.
(2) Third-stage turbine
wheel assembly.
(3) Fourth-stage turbine
wheel assembly.
6847142 and
6876892.
6845883 and
6849743.
6876468 ....................
Remove from service before or upon accumulating 16,000 cycles-in-service (CIS).
Remove from service before or upon accumulating 13,000 CIS.
Remove from service before or upon accumulating 24,000 CIS.
Remove from service before or upon accumulating 12,000 CIS.
Remove from service before or upon accumulating 10,000 CIS.
Remove from service before or upon accumulating 18,000 CIS.
501–D22 Series Engines
(g) For 501–D22 series engines, remove
turbine wheels and spacers from service as
specified in the following Table 2:
TABLE 2.—501–D22 SERIES LIFE LIMITS
Part name
Part number
(1) Third-stage turbine wheel assembly.
(2) 1st–2nd-stage spacer assembly
6855083 .........................................
Before or upon accumulating 10,000 cycles-in-service (CIS).
Before or upon accumulating 4,700 CIS.
(3) 1st–2nd-stage spacer assembly
6844632, 23033463, 23064854,
and 23064858.
23056966 .......................................
(4) 2nd–3rd-stage spacer assembly
(5) 2nd–3rd-stage spacer assembly
(6) 3rd–4th-stage spacer assembly
23033456 .......................................
23033464 and 6842683 ................
6844794 prior to revision letter ‘‘R’’
Alternative Methods of Compliance
(h) The Manager, Chicago Aircraft
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.
Remove from service
DEPARTMENT OF HOMELAND
SECURITY
Coast Guard
33 CFR Part 117
Related Information
[CGD13–06–006]
(i) Information on 501–D13 series engine
turbine life limits can be found in RRC
Commercial Service Letter (CSL) No. CSL–
120, Revision No. 52, dated July 22, 2002.
(j) Information on 501–D22 series engine
turbine life limits can be found in RRC CSL
No. CSL–1001, Revision No. 20, dated April
5, 2005.
RIN 1625–AA09
Issued in Burlington, Massachusetts, on
February 14, 2006.
Ann C. Mollica,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E6–2454 Filed 2–21–06; 8:45 am]
BILLING CODE 4910–13–P
cprice-sewell on PROD1PC66 with PROPOSALS
(i) Before or upon accumulating 8,000 CIS.
(ii) If the 1st–2nd-stage spacer assembly passes the hardness criteria
in RRC Commercial Engine Bulletin CEB–A–72–1135, then before
or upon accumulating 10,000 CIS.
Before or upon accumulating 4,200 CIS.
Before or upon accumulating 5,200 CIS.
Before or upon accumulating 5,100 CIS.
VerDate Aug<31>2005
14:42 Feb 21, 2006
Jkt 208001
Drawbridge Operation Regulations;
Hoquiam River, WA
Coast Guard, DHS.
Notice of proposed rulemaking.
AGENCY:
ACTION:
SUMMARY: The Coast Guard proposes to
temporarily modify the drawbridge
operation regulations for the Simpson
Avenue Bridge across the Hoquiam
River, mile 0.5, at Hoquiam,
Washington. The proposed temporary
change will enable the bridge owner to
delay openings of the bridge from May
1, 2006, through June 1, 2007. This will
facilitate major structural and
mechanical rehabilitation of the bascule
bridge.
DATES: Comments and related material
must reach the Coast Guard on or before
March 24, 2006.
ADDRESSES: You may mail comments
and related material to Commander
(dpw), 13th Coast Guard District, 915
Second Avenue, Seattle, WA 98174–
PO 00000
Frm 00057
Fmt 4702
Sfmt 4702
1067 where the public docket for this
rulemaking is maintained. Comments
and material received from the public,
as well as documents indicated in this
preamble as being available in the
docket, will become part of this docket
and will be available for inspection or
copying at the Waterways Management
Branch between 7:30 a.m. and 4 p.m.,
Monday through Friday, except Federal
holidays.
FOR FURTHER INFORMATION CONTACT:
Austin Pratt, Chief, Bridge Section,
(206) 220–7282.
SUPPLEMENTARY INFORMATION:
Request for Comments
We encourage you to participate in
this rulemaking by submitting
comments and related material. If you
do so, please include your name and
address, identify the docket number for
this rulemaking [CGD13–06–006],
indicate the specific section of this
document to which each comment
applies, and give the reason for each
comment. Please submit all comments
and related material in an unbound
format, no larger than 81⁄2 by 11 inches,
suitable for copying. If you would like
to know they reached us, please enclose
a stamped, self-addressed postcard or
envelope. We will consider all
comments and material received during
E:\FR\FM\22FEP1.SGM
22FEP1
]]>Agencies
[Federal Register Volume 71, Number 35 (Wednesday, February 22, 2006)]
[Proposed Rules]
[Pages 9048-9050]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-2454]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NE-01-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Corporation (Formerly
Allison Engine Company) 501-D Series Turboprop Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) for Rolls-Royce Corporation (formerly Allison Engine
Company) (RRC) 501-D series turboprop engines. That AD currently
requires removal from service of certain turbine rotor components at
reduced life limits. This proposed AD would require the same actions
but adds two new life limits. This proposed AD results from RRC
reevaluating and revising component life limits for 501-D22 series
turboprop engines. We are proposing this AD to prevent uncontained
turbine rotor failure resulting in an in-flight engine shutdown and
possible damage to the airplane.
DATES: We must receive any comments on this proposed AD by April 24,
2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
By mail: Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 2001-NE-01-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
By fax: (781) 238-7055.
By e-mail: 9-ane-adcomment@faa.gov.
You can get the service information identified in this proposed AD
from Rolls-Royce Corporation, P.O. Box 420, Indianapolis, IN 46206-
0420; telephone (317) 230-6400; fax (317) 230-4243.
You may examine the AD docket at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA.
FOR FURTHER INFORMATION CONTACT: Michael Downs, Aerospace Engineer,
Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des
Plaines, IL 60018; telephone (847) 294-7870; fax (847) 294-7834.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 2001-NE-01-AD'' in the
subject line of your comments. If you want us to acknowledge receipt of
your mailed comments, send us a self-addressed, stamped postcard with
the docket number written on it; we will date-stamp your postcard and
mail it back to you. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. If a person contacts us verbally, and that contact relates to a
substantive part of this proposed AD, we will summarize the contact and
place the summary in the docket. We will consider all comments received
by the closing date and may amend the proposed AD in light of those
comments.
Examining the AD Docket
You may examine the AD Docket (including any comments and service
information), by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.
Discussion
On March 25, 2003, we issued AD 2003-07-02, Amendment 39-13098 (68
FR 15937, April 2, 2003). That AD requires removing from service
certain turbine rotor components at reduced life limits. That AD
resulted from RRC updating material properties and recalculating
component life limits. That condition, if not corrected, could result
in uncontained turbine rotor
[[Page 9049]]
failure resulting in an in-flight engine shutdown and possible damage
to the airplane.
Actions Since AD 2003-07-02 Was Issued
Since we issued AD 2003-07-02, RRC reevaluated turbine wheel
assembly and turbine wheel spacer assembly life limits for 501-D series
turboprop engines. RRC changed certain life limits for the 501-D22
series turboprop engines because of recent improvements in how low-
cycle-fatigue life is determined. RRC similarly reduced the life limit
of 2nd-3rd-stage spacer assemblies, part numbers (P/Ns) 23033464 and
6842683, installed on 501-D22 series turboprop engines.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. We are proposing this AD, which would require
the same actions specified in AD 2003-07-02, but for 501-D22 series
turboprop engines, it would add a life limit of 5,200 cycles-in-service
for 2nd-3rd-stage spacer assemblies, P/Ns 23033464 and 6842683.
Costs of Compliance
We estimate that this proposed AD would affect 684 engines
installed on aircraft of U.S. registry. The proposed action does not
impose any additional labor costs if performed at the time of scheduled
engine overhaul. Required parts would cost about $45,000 per engine.
Based on these figures, we estimate the total cost of the proposed AD
to U.S. operators to be $30,780,000.
Special Flight Permits Paragraph Removed
Paragraph (f) of the current AD, AD 2003-07-02, contains a
paragraph pertaining to special flight permits. Even though this
proposed AD does not contain a similar paragraph, we have made no
changes with regard to the use of special flight permits to operate the
airplane to a repair facility to do the work required by this proposed
AD. In July 2002, we published a new Part 39 that contains a general
authority regarding special flight permits and airworthiness
directives; see Docket No. FAA-2004-8460, Amendment 39-9474 (69 FR
47998, July 22, 2002). Thus, when we now supersede ADs we will not
include a specific paragraph on special flight permits unless we want
to limit the use of that general authority granted in section 39.23.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify that the proposed
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. Would 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 proposal and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 2001-NE-01-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 14
CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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]
2. The FAA amends Sec. 39.13 by removing Amendment 39-13098 (68 FR
15937, April 2, 2003) and by adding a new airworthiness directive to
read as follows:
Rolls-Royce Corporation: Docket No. 2001-NE-01-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by April 24,
2006.
Affected ADs
(b) This AD supersedes AD 2003-07-02, Amendment 39-13098.
Applicability
(c) This AD applies to Rolls-Royce Corporation (formerly Allison
Engine Company) (RRC) 501-D series turboprop engines. These engines
are installed on, but not limited to, Lockheed 188 series and 382
series turboprop airplanes, Airbus 377SG5-F (Super Guppy) airplanes,
and Convair Models 340 and 440 airplanes which have RRC 501-D series
turboprop engines installed under Supplemental Type Certificate No.
SE1161EA. These latter models are commonly referred to as Convair
580/580A or 5800 models.
(d) This AD results from RRC reevaluating and revising component
life limits for 501-D22 series turboprop engines. We are issuing
this AD to prevent uncontained turbine rotor failure resulting in an
in-flight engine shutdown and possible 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.
501-D13 Series Engines
(f) For 501-D13 series engines, remove turbine wheels and
spacers from service as specified in the following Table 1:
[[Page 9050]]
Table 1.--501-D13 Series Life Limits
----------------------------------------------------------------------------------------------------------------
Life limit for wheels
that have complied with Life limit for wheels
commercial overhaul that have not complied
Part name Part number information letter with COIL 401, dated
(COIL) 401, dated May May 1978
1978
----------------------------------------------------------------------------------------------------------------
(1) Second-stage turbine wheel 6847142 and 6876892.......... Remove from service Remove from service
assembly. before or upon before or upon
accumulating 16,000 accumulating 12,000
cycles-in-service CIS.
(CIS).
(2) Third-stage turbine wheel 6845883 and 6849743.......... Remove from service Remove from service
assembly. before or upon before or upon
accumulating 13,000 accumulating 10,000
CIS. CIS.
(3) Fourth-stage turbine wheel 6876468...................... Remove from service Remove from service
assembly. before or upon before or upon
accumulating 24,000 accumulating 18,000
CIS. CIS.
----------------------------------------------------------------------------------------------------------------
501-D22 Series Engines
(g) For 501-D22 series engines, remove turbine wheels and
spacers from service as specified in the following Table 2:
Table 2.--501-D22 Series Life Limits
------------------------------------------------------------------------
Part name Part number Remove from service
------------------------------------------------------------------------
(1) Third-stage turbine wheel 6855083.......... Before or upon
assembly. accumulating 10,000
cycles-in-service
(CIS).
(2) 1st-2nd-stage spacer 6844632, Before or upon
assembly. 23033463, accumulating 4,700
23064854, and CIS.
23064858.
(3) 1st-2nd-stage spacer 23056966......... (i) Before or upon
assembly. accumulating 8,000
CIS.
(ii) If the 1st-2nd-
stage spacer
assembly passes the
hardness criteria in
RRC Commercial
Engine Bulletin CEB-
A-72-1135, then
before or upon
accumulating 10,000
CIS.
(4) 2nd-3rd-stage spacer 23033456......... Before or upon
assembly. accumulating 4,200
CIS.
(5) 2nd-3rd-stage spacer 23033464 and Before or upon
assembly. 6842683. accumulating 5,200
CIS.
(6) 3rd-4th-stage spacer 6844794 prior to Before or upon
assembly. revision letter accumulating 5,100
``R''. CIS.
------------------------------------------------------------------------
Alternative Methods of Compliance
(h) The Manager, Chicago Aircraft 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) Information on 501-D13 series engine turbine life limits can
be found in RRC Commercial Service Letter (CSL) No. CSL-120,
Revision No. 52, dated July 22, 2002.
(j) Information on 501-D22 series engine turbine life limits can
be found in RRC CSL No. CSL-1001, Revision No. 20, dated April 5,
2005.
Issued in Burlington, Massachusetts, on February 14, 2006.
Ann C. Mollica,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E6-2454 Filed 2-21-06; 8:45 am]
BILLING CODE 4910-13-P
