Airworthiness Directives; Rolls-Royce Corporation 501-D Series Turboprop Engines, 75855-75857 [E6-21352]

Download as PDF Federal Register / Vol. 71, No. 243 / Tuesday, December 19, 2006 / Rules and Regulations 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 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: cprice-sewell on PROD1PC66 with RULES I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I VerDate Aug<31>2005 14:56 Dec 18, 2006 Jkt 211001 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 75855 alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. I 2. The FAA amends § 39.13 by adding the following new airworthiness directive: Related Information (j) None. 2006–26–01 CFM International, S.A.: Amendment 39–14859. Docket No. FAA–2006–26502; Directorate Identifier 2006–NE–37–AD. Material Incorporated by Reference (k) None. Effective Date (a) This airworthiness directive (AD) becomes effective January 3, 2007. Affected ADs (b) None. BILLING CODE 4910–13–P Applicability (c) This AD applies to CFM International CFM56–2 series, –3 series, –5 series, and –7B series engines with fuel filters, Western Filter part numbers (P/Ns) WF337661 and WF337017 and PTI Technologies P/Ns 7595983–101 and 7588133, installed. These engines are installed on, but not limited to, Airbus A320 and A340 series airplanes, Boeing DC8–71 series, –72 series, and –73 series airplanes, and Boeing 737 series airplanes. Unsafe Condition (d) This AD results from 12 reports of failed fuel filters. We are issuing this AD to prevent the loss of engine thrust that could result in loss of control during takeoff or landing. 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. Replacing the Fuel Filters on CFM56–7B Engines (f) For CFM56–7B engines, within 600 flight hours or 60 days after the effective date of this AD, whichever occurs first, replace fuel filter, Western Filter P/Ns WF337661 or WF337017 and PTI Technologies P/Ns 7595983–101 or 7588133, with a filter that has a P/N not listed in this AD. Replacing the Fuel Filters on CFM56–2, –3, and –5 Series Engines (g) For CFM56–2 series, –3 series, and –5 series engines, at the next filter change or 4,000 flight hours, whichever occurs first, after the effective date of this AD, replace fuel filter, Western Filter P/Ns WF337661 or WF337017 and PTI Technologies P/Ns 7595983–101 or 7588133, with a filter that has a P/N not listed in this AD. Prohibition Against Installing Fuel Filters with Certain P/Ns (h) After the effective date of this AD, do not install any fuel filter, Western Filter P/ Ns WF337661 or WF337017 or PTI Technologies P/Ns 7595983–101 or 7588133. Alternative Methods of Compliance (i) The Manager, Engine Certification Office, has the authority to approve PO 00000 Frm 00005 Issued in Burlington, Massachusetts, on December 12, 2006. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6–21485 Filed 12–18–06; 8:45 am] Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26193; Directorate Identifier 2001–NE–01–AD; Amendment 39– 14853; AD 2006–25–12] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Corporation 501–D Series Turboprop Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce Corporation (RRC) 501–D series turboprop engines. That AD requires removal from service of certain turbine rotor components at reduced life limits. This AD requires the same actions but adds two new life limits. 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. DATES: This AD becomes effective January 23, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of January 23, 2007. ADDRESSES: You can get the service information identified in this AD from Rolls-Royce Corporation, P.O. Box 420, 2001 South Tibbs Avenue, Indianapolis, IN 46206–0420; telephone (317) 230– 2000; fax (317) 230–4020 for the service information identified in this AD. You may examine the AD docket on the Internet at https://dms.dot.gov or in Room PL–401 on the plaza level of the E:\FR\FM\19DER1.SGM 19DER1 75856 Federal Register / Vol. 71, No. 243 / Tuesday, December 19, 2006 / Rules and Regulations Nassif Building, 400 Seventh Street, SW., Washington, DC. 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: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to RRC 501–D series turboprop engines. We published the proposed AD in the Federal Register on February 22, 2006 (71 FR 9048). That action proposed to require removal from service of certain turbine rotor components at reduced life limits, the same as AD 2003–07–02, but would add two new life limits. 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 Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the proposal or on the determination of the cost to the public. Incorrect Supplemental Type Certificate (STC) Number Since we issued the proposed AD, we became aware that the STC number SE1161EA, referenced in paragraph (c), is incorrect. We corrected the number to STC SA4–1100 in the AD. cprice-sewell on PROD1PC66 with RULES Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD with the change described previously. Costs of Compliance We estimate that this AD will affect 684 engines installed on aircraft of U.S. registry. The action does not impose any additional labor costs if performed at the time of scheduled engine overhaul. Required parts will cost about $45,000 per engine. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $30,780,000. VerDate Aug<31>2005 14:56 Dec 18, 2006 Jkt 211001 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 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 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. the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. Docket Number Change We are transferring the docket for this AD to the Docket Management System as part of our on-going docket management consolidation efforts. The new Docket No. is FAA–2006–26193. The old Docket No. became the Directorate Identifier, which is 2001– NE–01–AD. This AD might get logged into the DMS docket, ahead of the previously collected documents from the old docket file, as we are in the process of sending those items to the DMS. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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. Authority: 49 U.S.C. 106(g), 40113, 44701. 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 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 List of Subjects in 14 CFR Part 39 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I § 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, Amendment 39–14853, to read as follows: I 2006–25–12 Rolls-Royce Corporation (formerly Allison Engine Company): Amendment 39–14853. Docket No. FAA–2006–26193; Directorate Identifier 2001–NE–01–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 23, 2007. 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 E:\FR\FM\19DER1.SGM 19DER1 Federal Register / Vol. 71, No. 243 / Tuesday, December 19, 2006 / Rules and Regulations installed under Supplemental Type Certificate No. SA4–1100. 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 501D22 series turboprop engines. We are issuing 75857 this AD to prevent uncontained turbine rotor failure resulting in an in-flight engine shutdown and possible damage to the airplane. the compliance times specified unless the actions have already been done. Compliance (e) You are responsible for having the actions required by this AD performed within (f) For 501–D13 series engines, remove turbine wheels and spacers from service as specified in the following Table 1: 501–D13 Series Engines TABLE 1.—501–D13 SERIES LIFE LIMITS Life limit for wheels that have complied with commercial overhaul information letter (COIL) 401, dated May 1978 Part name Part No. (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 ..................... Life limit for wheels that have not complied with COIL 401, dated May 1978 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 No. (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. cprice-sewell on PROD1PC66 with RULES 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. Material Incorporated by Reference (k) You must use Rolls-Royce Corporation Commercial Engine Bulletin No. CEB–A–72– 1135, Revision 2, dated July 11, 2003, to check if 1st–2nd stage spacer assemblies pass the hardness criteria required by Table 2 of this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Rolls-Royce Corporation, P.O. Box 420, 2001 South Tibbs Avenue, Indianapolis, IN 46206– VerDate Aug<31>2005 14:56 Dec 18, 2006 Jkt 211001 Remove from service (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 No. CEB–A–72–1135, Revision 2, dated July 11, 2003, 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. 0420; telephone (317) 230–2000; fax (317) 230–4020 for a copy of this service information. You may review copies at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. DEPARTMENT OF TRANSPORTATION Issued in Burlington, Massachusetts, on December 11, 2006. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6–21352 Filed 12–18–06; 8:45 am] Revision of Class E Airspace; Homer, AK BILLING CODE 4910–13–P SUMMARY: This action revises Class E airspace at Homer, AK to provide adequate controlled airspace to contain aircraft executing four new Standard Instrument Approach Procedures (SIAPs). This rule results in the revision of Class E airspace upward from the surface, from 700 feet (ft.), and from 1,200 ft. above the surface at Homer, AK. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2006–25762; Airspace Docket No. 06–AAL–25] Federal Aviation Administration (FAA), DOT. AGENCY: ACTION: E:\FR\FM\19DER1.SGM Final rule. 19DER1

Agencies

[Federal Register Volume 71, Number 243 (Tuesday, December 19, 2006)]
[Rules and Regulations]
[Pages 75855-75857]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-21352]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26193; Directorate Identifier 2001-NE-01-AD;
Amendment 39-14853; AD 2006-25-12]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce Corporation 501-D Series
Turboprop Engines

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for Rolls-Royce Corporation (RRC) 501-D series turboprop engines.
That AD requires removal from service of certain turbine rotor
components at reduced life limits. This AD requires the same actions
but adds two new life limits. 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.

DATES: This AD becomes effective January 23, 2007. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of January 23, 2007.

ADDRESSES: You can get the service information identified in this AD
from Rolls-Royce Corporation, P.O. Box 420, 2001 South Tibbs Avenue,
Indianapolis, IN 46206-0420; telephone (317) 230-2000; fax (317) 230-
4020 for the service information identified in this AD.
You may examine the AD docket on the Internet at https://dms.dot.gov
or in Room PL-401 on the plaza level of the

[[Page 75856]]

Nassif Building, 400 Seventh Street, SW., Washington, DC.

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: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to RRC 501-D series
turboprop engines. We published the proposed AD in the Federal Register
on February 22, 2006 (71 FR 9048). That action proposed to require
removal from service of certain turbine rotor components at reduced
life limits, the same as AD 2003-07-02, but would add two new life
limits.

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 Offices between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone (800)
647-5227) is located on the plaza level of the Department of
Transportation Nassif Building at the street address stated in
ADDRESSES. Comments will be available in the AD docket shortly after
the DMS receives them.

Comments

We provided the public the opportunity to participate in the
development of this AD. We received no comments on the proposal or on
the determination of the cost to the public.

Incorrect Supplemental Type Certificate (STC) Number

Since we issued the proposed AD, we became aware that the STC
number SE1161EA, referenced in paragraph (c), is incorrect. We
corrected the number to STC SA4-1100 in the AD.

Conclusion

We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD with the
change described previously.

Costs of Compliance

We estimate that this AD will affect 684 engines installed on
aircraft of U.S. registry. The action does not impose any additional
labor costs if performed at the time of scheduled engine overhaul.
Required parts will cost about $45,000 per engine. Based on these
figures, we estimate the total cost of the 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 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 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.

Docket Number Change

We are transferring the docket for this AD to the Docket Management
System as part of our on-going docket management consolidation efforts.
The new Docket No. is FAA-2006-26193. The old Docket No. became the
Directorate Identifier, which is 2001-NE-01-AD. This AD might get
logged into the DMS docket, ahead of the previously collected documents
from the old docket file, as we are in the process of sending those
items to the DMS.

Authority for This Rulemaking

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

Regulatory Findings

We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

0
2. The FAA amends Sec. 39.13 by removing Amendment 39-13098 (68 FR
15937, April 2, 2003), and by adding a new airworthiness directive,
Amendment 39-14853, to read as follows:

2006-25-12 Rolls-Royce Corporation (formerly Allison Engine
Company): Amendment 39-14853. Docket No. FAA-2006-26193; Directorate
Identifier 2001-NE-01-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective January
23, 2007.

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

[[Page 75857]]

installed under Supplemental Type Certificate No. SA4-1100. 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:

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 No. 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 No. 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 No.
CEB-A-72-1135,
Revision 2, dated
July 11, 2003, 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.

Material Incorporated by Reference

(k) You must use Rolls-Royce Corporation Commercial Engine
Bulletin No. CEB-A-72-1135, Revision 2, dated July 11, 2003, to
check if 1st-2nd stage spacer assemblies pass the hardness criteria
required by Table 2 of this AD. The Director of the Federal Register
approved the incorporation by reference of this service bulletin in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Rolls-
Royce Corporation, P.O. Box 420, 2001 South Tibbs Avenue,
Indianapolis, IN 46206-0420; telephone (317) 230-2000; fax (317)
230-4020 for a copy of this service information. You may review
copies at the National Archives and Records Administration (NARA).
For information on the availability of this material at NARA, call
202-741-6030, or go to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.

Issued in Burlington, Massachusetts, on December 11, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E6-21352 Filed 12-18-06; 8:45 am]
BILLING CODE 4910-13-P

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.