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


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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.

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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 http://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
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                                                                 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
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(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
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           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: http://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]
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