Federal Register, Volume 68 Issue 63 (Wednesday, April 2, 2003)

[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

[[Page 15938]]

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

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

[[Page 15939]]

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