[Federal Register Volume 68, Number 63 (Wednesday, April 2, 2003)]
[Rules and Regulations]
[Pages 15937-15939]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-7743]



[[Page 15937]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-01-AD; Amendment 39-13098; AD 2003-07-02]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Corporation (Formerly 
Allison Engine Company) 501-D Series Turboprop Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), that 
is applicable to Rolls-Royce Corporation (formerly Allison Engine 
Company) 501-D series turboprop engines. This amendment requires 
removal from service of certain turbine rotor components at reduced 
life limits. This amendment is prompted by the result of recalculated 
material properties by the manufacturer. The actions specified by this 
AD are intended to prevent uncontained turbine rotor failure resulting 
in in-flight engine shutdown and possible damage to the airplane.

DATES: Effective May 7, 2003.

ADDRESSES: The service information referenced in this AD may be 
obtained from Rolls-Royce Corporation, PO Box 420, Indianapolis, IN 
46206-0420; telephone (317) 230-6400; fax (317) 230-4243. This 
information may be examined, by appointment, at the Federal Aviation 
Administration (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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an AD that is 
applicable to Rolls-Royce Corporation (formerly Allison Engine Company) 
501-D series turboprop engines was published in the Federal Register on 
October 18, 2002 (67 FR 64328). That action proposed to require removal 
from service of certain turbine rotor components at reduced life limits 
due to recalculated material properties by the manufactuer. As a 
result, the manufacturer has reduced the life limits of certain second-
stage, third-stage, and fourth-stage turbine wheel assemblies, and 
certain 1st-2nd stage, 2nd-3rd stage, and 3rd-4th stage turbine spacer 
assemblies.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

AD Not Required

    One commenter states that it is a waste of tax dollars to issue the 
AD when the life limits of Rolls-Royce Customer Service Letter (CSL) 
1001, Revision 19, dated July 22, 2002, and the life limit reduction 
specified by the NRPM are the same. The commenter continues to say that 
the only possible difference the AD could address would be the ``one 
time exception'' permitted by the CSL to operate beyond the revised 
limits until March 31, 2003, and then only if the AD is adopted as a 
final rule before March 31, 2003. The commenter believes that the AD 
does not offer any new information except that the FAA may address the 
``one time exception'' permitted by CSL 1001.
    The FAA does not agree. Whenever the FAA lowers the life of 
critical service parts, an AD is required because the change in service 
life has become more restricted. The reason CSL 1001 and the NPRM are 
the same is because Rolls-Royce has already revised the CSL as a result 
of the NPRM. The AD is not addressing the ``one time exception'' in CSL 
1001, Revision 19, dated July 22, 2002.

Expand the Applicability To Add Airbus Industrie 377S GT-F (Super 
Guppy)

    One commenter requests that the Applicability statement be written 
to include the Airbus Industrie 377SGT-F (Super Guppy) model.
    The FAA agrees. The Applicability statement is revised to reflect 
this change.

Add Assigned Rework Part Numbers to Table 2

    One commenter requests that two additional part numbers (PNs) 
23064854 and 23064858, be added to the Supplementary Information 
section ``FAA's Determination of an Unsafe Condition and Proposed 
Actions'' and that the same numbers be added to Table 2 501-D22 Series 
Life Limits. The two additional PNs are the assigned reworked PNs for 
6844632 and 23033463. The reworked PNs have the same life limit as 
their prior part number; therefore, they should be added to the AD to 
prevent any confusion regarding their reduction in life limit to 4,700 
cycles-in-service (CIS).
    The FAA agrees. The assigned reworked PNs are added to Table 2; 
however the FAA's Determination of an Unsafe Condition and Proposed 
Actions section in the NPRM preamble does not appear in the final rule.

Original Life Limit for Part Number 6844794 Rev R and Greater

    The same commenter requests an additional change to the 
Supplementary Information Section ``FAA's Determination of an Unsafe 
Condition and Proposed Actions'' and to Table 2. The commenter states 
that the life limit reduction for the PN 6844794, 3rd and 4th stage 
turbine spacer is only necessary for those parts which were 
manufactured prior to part number drawing 6844794 revision letter 
``R''. Tighter dimensional control of the spacer critical life location 
which was implemented with PN 6844794 revision letter ``R'' allows PNs 
identified as Rev ``R'' and greater to remain at their previous life 
limits. Therefore, the commenter requests that delineation by PN 
6844794 ``with serial number (SN) less than and including KK22951 * * 
*'' be replaced by ``PN 6844794 prior to revision letter R''.
    The FAA agrees. Table 2 reflects the change in the AD; however, the 
FAA's Determination of an Unsafe Condition and Proposed Actions section 
in the NPRM preamble does not appear in the final rule.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Economic Analysis

    There are approximately 930 Rolls-Royce 501-D series turboprop 
engines of the affected design in the worldwide fleet. The FAA 
estimates that 684 engines installed on airplanes of U.S. registry will 
be affected by this AD. This AD does not impose any additional labor 
costs if performed at the time of scheduled engine overhaul. Required 
parts will cost approximately $45,000 per engine. Based on these 
figures, the total cost of the AD to U.S. operators is estimated to be 
$30,780,000.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it

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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. Accordingly, the FAA has not consulted with state 
authorities prior to publication of this final rule.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
by contacting the Rules Docket at the location provided under the 
caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2003-07-02 Rolls-Royce Corporation: Amendment 39-13098. Docket No. 
2001-NE-01-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Rolls-Royce Corporation (formerly Allison Engine Company) 501-D 
series turboprop engines. These engines are installed on, but not 
limited to Lockheed 188 series and 382 series turboprop airplanes, 
Airbus Industrie 377SG5-F (Super Guppy) airplanes, and Convair 
Models 340 and 440 airplanes which have Rolls-Royce corporation 501-
D series turboprop engines installed under a Supplemental Type 
Certificate. These models are commonly referred to as Convair 580/
580A or 5800 models.

    Note 1: This AD applies to each engine identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For engines that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (e) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Compliance with this AD is required as indicated, 
unless already done.
    To prevent uncontained turbine rotor failure, resulting in in-
flight engine shutdown and possible damage to the airplane, do the 
following:

501-D13 Series Engines

    (a) 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
----------------------------------------------------------------------------------------------------------------
(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.
----------------------------------------------------------------------------------------------------------------

    (b) Information on 501-D13 series engine turbine life limits can 
be found in Rolls-Royce Commercial Service Letter (CSL) No. CSL-120, 
Revision No. 52, dated July 22, 2002.

501-D22 Series Engines

    (c) 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.........  Before or upon
 assembly.                                          accumulating 8,000
                                                    CIS.
(4) 2nd-3rd-stage spacer        23033456.........  Before or upon
 assembly.                                          accumulating 4,000
                                                    CIS.
(5) 3rd-4th-stage spacer        6844794 prior to   Before or upon
 assembly.                       revision letter    accumulating 5,100
                                 ``R''.             CIS.
------------------------------------------------------------------------

    (d) Information on 501-D22 series engine turbine life limits can 
be found in Rolls-Royce Commercial Service Letter (CSL) No. CSL-
1001, Revision No. 19, dated July 22, 2002.

Alternative Methods of Compliance

    (e) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Chicago Aircraft Certification 
Office (ACO). Operators must submit their request through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of

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compliance with this airworthiness directive, if any, may be 
obtained from the ACO.

Special Flight Permits

    (f) Special flight permits may be issued in accordance with 
Sec. Sec.  21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be done.

Effective Date

    (g) This amendment becomes effective on May 7, 2003.

    Issued in Burlington, Massachusetts, on March 25, 2003.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-7743 Filed 4-1-03; 8:45 am]
BILLING CODE 4910-13-P