[Federal Register Volume 63, Number 232 (Thursday, December 3, 1998)]
[Rules and Regulations]
[Pages 66735-66737]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-31702]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-ANE-23-AD; Amendment 39-10915; AD 98-24-28]
RIN 2120-AA64
Airworthiness Directives; Allison Engine Company 250-B and 250-C
Series Turboshaft and Turboprop Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Allison Engine Company 250-B and 250-C series
turboshaft and turboprop engines, that requires replacing existing
beryllium copper main fuel control (MFC) bellows assemblies with
Inconel 718 stainless steel welded MFC bellows assemblies. This
amendment is prompted by reports of leaking MFC bellows assemblies
resulting in an uncommanded minimum fuel flow condition, loss of engine
fuel flow control and subsequent forced landing. The actions specified
by this AD are intended to prevent MFC bellows assembly leakage, which
can result in an uncommanded minimum fuel flow condition and subsequent
loss of engine fuel flow control.
DATES: Effective January 7, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 7, 1999.
ADDRESSES: The service information referenced in this AD may be
obtained from Allison Engine Company, P.O. Box 420, Speed Code U-15,
Indianapolis, IN 46206-0420, telephone (317) 230-6674. This information
may be examined at the Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, 12 New England
Executive Park, Burlington, MA; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: John Tallarovic, Aerospace Engineer,
Chicago Aircraft Certification Office, FAA, Small Airplane Directorate,
2350 E. Devon Avenue, Room 323, Des Plaines, IL 60018; telephone (847)
294-8180, fax (847) 294-7834.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Allison Engine Company
250-B and 250-C series turboshaft engines was published in the Federal
Register on June 8, 1998 (63 FR 31138). That action proposed to require
replacing the existing beryllium copper main fuel control (MFC) bellows
assemblies at the next repair or overhaul of the MFC bellows assembly,
or, since corrosion was a factor, by the calendar end-dates specified,
whichever occurs first. Since that issuance of that proposal, the FAA
has discovered that the turboprop aircraft were inadvertently omitted
from the
[[Page 66736]]
applicability section, which has been corrected is this final rule.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal or the FAA's determination of the cost to the public. This
final rule references only one Allison Commercial Engine Bulletin (CEB)
CEB-A-282, Revision 2, dated April 15, 1998, that also serves as the
seven other CEBs listed in paragraph (b) of the proposed rule. It
serves as the cover document for the AlliedSignal Aerospace Equipment
Systems service bulletin GT-242, revision 2, dated April 15, 1998, the
manufacturer of the MFC. The FAA has determined that these changes will
neither increase the economic burden on any operator nor increase the
scope of the AD.
The FAA estimates that 2,500 engines installed on aircraft of U.S.
registry will be affected by this AD, that it will take no additional
work hours per engine to accomplish the proposed actions at regularly
scheduled overhaul, and required parts would cost approximately $1,495
per engine. Based on these figures, the total cost impact of the AD on
U.S. operators is estimated to be $3,737,500.
The regulations adopted herein will not have substantial direct
effects 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. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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 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
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air Transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
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
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. Section 39.13 is amended by adding the following new
airworthiness directive:
98-24-28 Allison Engine Company: Amendment 39-10915. Docket 98-ANE-
23-AD.
Applicability: Allison Engine Company 250-B15, 250-B17, 250-
B17F, series turboprop engines and 250-C18, 250-C20, 250-C20R, 250-
C28, 250-C30 series turboshaft engines, installed on but not limited
to AeroSpace Technologies of Australia Pty Ltd Models N22B, N22S,
and N24A; Beech Aircraft Corporation Model 35; Cessna Aircraft
Company Model 210; Maule Aerospace Technology Corp. Models MX-7-420
and MXT-7-420; Partenavia Construzioni Aeronauticas S.p.A. Models
AP68TP 300 and AP68TP 600; Pilatus Britten-Norman Models BN-2T and
BN-2T-4R; SIAI Marchetti S.r.l. Models SF600 and SF600A airplanes;
AGUSTA Models A109, A109A, A109AII, A109C; Bell Helicopter Textron
Models 47, 206, 206A, 206B, 206L, 206L-1, 206L-4, 230; Enstrom
Helicopter Models TH-28 and 480; Eurocopter Canada Model BO 105 LS
A-3; Eurocopter Deutschland Models BO-105A, BO-105C, BO-105S and BO-
105LS A-1; Eurocopter France Models AS355E, AS355F, AS355F1 and
AS355F2; Hiller Model FH-1100; McDonnell Douglas Helicopter Company
Models 369D, 369E, 369F, 369H, 369HM, 369HS, 369HE, 369FF, 500N;
Rogerson Hiller Corp. Model UH-12E, Schweizer Model 269D; and
Sikorsky Model S-76A rotorcraft; and Lockheed Martin Tactical
Defense System Model GZ-22 airship.
Note 1: This airworthiness directive (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 (c) 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: Required as indicated, unless accomplished
previously.
To prevent main fuel control (MFC) bellows assembly leakage,
which can result in an uncommanded minimum fuel flow condition and
subsequent loss of engine fuel flow control, accomplish the
following:
(a) Replace existing beryllium copper MFC bellows assemblies,
part numbers (P/Ns) 2523722, 2539647, 2540539, 2540767, and 2542526,
with Inconel 718 stainless steel welded MFC bellows assemblies, P/N
2543598, in accordance with Allison Commercial Engine Bulletin (CEB)
CEB-A-282/AlliedSignal Aerospace Equipment Systems Service Bulletin
(SB) GT-242, Revision 2, dated April 15, 1998, at the earlier of the
following:
(1) The next time after the effective date of this AD the MFC is
being repaired or overhauled; or
(2) The following populations of MFCs, as applicable
(i) All MFCs listed by P/Ns in Tables 1 and 2 of the CEB/SB by
March 31, 1999; or
(ii) All MFCs listed by P/Ns in Table 3 of the CEB/SB by August
31, 1999.
(iii) All MFCs listed by P/Ns in Tables 4 and 5 of the CEB/SB by
October 31, 1999.
Note 2: Allison CEB-A-282, Revision 2, dated April 15, 1998,
also serves as CEB-A-1329 for the 250-C20 series engines, CEB-A-73-
2053 for the 250-C28 series engines, CEB-A-73-3068 for the 250-C30
series engines, CEB-A-73-4029 for the 250-C20R series engines,
Turboprop (TP) CEB-A-158 for the 250-B15G series engines, TP CEB-A-
1286 for the 250-B17 series engines, and TP CEB-A-73-2014 for the
250-B17F series engines.
(b) Perform the replacement of MFC bellows assemblies required
by paragraph (a) of this AD in accordance with the accomplishment
instructions paragraph of Allison CEB-A-282/AlliedSignal Aerospace
Equipment Systems Service Bulletin (SB) SB GT-242 Revision 2, dated
April 15, 1998.
(c) 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. Operators shall submit their request through an appropriate
FAA Principal Maintenance Inspector, who may add comments and then
send it to the Manager, Chicago Aircraft Certification Office.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Chicago Aircraft Certification
Office.
(d) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the aircraft to a location where
the requirements of this AD can be accomplished.
(e) The actions required by this AD shall be done in accordance
with the following Allison Engine Company CEB/AlliedSignal Aerospace
Equipment Systems SB GT-242, Revision 2, dated April 15, 1998:
[[Page 66737]]
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Document No. Pages Revision Date
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CEB-A-282............................ 1-28................... 2...................... April 15, 1998
Total Pages: 28..................
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This incorporation by reference was approved by the Director of
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Copies may be obtained from Allison Engine Company, P.O.
Box 420, Speed Code U-15, Indianapolis, IN 46206-0420, telephone
(317) 230-6674. Copies may be inspected at the FAA, New England
Region, Office of the Regional Counsel, 12 New England Executive
Park, Burlington, MA; or at the Office of the Federal Register, 800
North Capitol Street NW., suite 700, Washington, DC.
(f) This amendment becomes effective on January 7, 1999.
Issued in Burlington, Massachusetts, on November 18, 1998.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 98-31702 Filed 12-2-98; 8:45 am]
BILLING CODE 4910-13-P
