Airworthiness Directives; Rolls-Royce Corporation (Formerly Allison Engine Company) 501-D Series Turboprop Engines, 9048-9050 [E6-2454]

Download as PDF 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