[Federal Register: December 29, 2005 (Volume 70, Number 249)]
[Proposed Rules]
[Page 77073-77075]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29de05-16]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-ANE-72-AD]
RIN 2120-AA64
Airworthiness Directives; Honeywell International Inc., (Formerly
AlliedSignal, Inc., Formerly Textron Lycoming, Formerly Avco Lycoming)
T5311A, T5311B, T5313B, T5317A, T5317A-1, T5317B Series Turboshaft
Engines and Lycoming Former Military T53-L-11B, T53-L-11D, T53-L-13B,
T53-L-13B/D, and T53-L-703 Series Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD), AD 98-22-11, for AlliedSignal, Inc. T5317A-1 turboshaft
engines. That AD currently requires repetitive engine fuel pump
pressure tests of certain fuel control regulator assemblies to
determine if both fuel pumps in the fuel control regulator assemblies
are producing fuel pressure. That AD also requires replacing the fuel
control regulator assembly, if necessary. This proposed AD would
require initial and repetitive visual and dimensional inspections of
fuel control regulator assembly main and secondary drive shaft and pump
gear splines, installed in certain fuel control regulator assemblies.
This proposed AD would also expand the engine applicability, and
include certain engines installed on helicopters certified under Sec.
21.25 or 21.27 of the Code of Federal Regulations (14 CFR 21.25 or 14
CFR 21.27). This proposed AD results from several reports of loss of
fuel flow from the engine fuel control regulator assembly due to
failure of both main and secondary drive shaft and pump gear splines.
We are proposing this AD to prevent in-flight engine failure and forced
autorotation landing.
DATES: We must receive any comments on this proposed AD by February 27,
2006.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
By mail: Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 98-ANE-72-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
By fax: (781) 238-7055.
By e-mail: 9-ane-adcomment@faa.gov.
Contact Honeywell International Inc., Attn: Data Distribution, M/S
64-3/2101-201, P.O. Box 29003, Phoenix, AZ 85038-9003; telephone: (602)
365-2493; fax:(602) 365-5577, for the service information identified in
this proposed AD.
You may examine the AD docket at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA.
FOR FURTHER INFORMATION CONTACT: Robert Baitoo, Aerospace Engineer, Los
Angeles Aircraft Certification Office, FAA, Transport Airplane
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; telephone:
(562) 627-5245, fax: (562) 627-5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 98-ANE-72-AD'' in the
subject line of your comments. If you want us to acknowledge receipt of
your mailed comments, send us a self-addressed, stamped postcard with
the docket number written on it; we will date-stamp your postcard and
mail it back to you. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. If a person contacts us
[[Page 77074]]
verbally, and that contact relates to a substantive part of this
proposed AD, we will summarize the contact and place the summary in the
docket. We will consider all comments received by the closing date and
may amend the proposed AD in light of those comments.
Examining the AD Docket
You may examine the AD Docket (including any comments and service
information), by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.
Discussion
On November 25, 1998, we issued AD 98-22-11, Amendment 39-10926 (63
FR 66741, December 3, 1998). That AD requires repetitive pressure
testing to determine if both fuel pumps in the fuel control regulator
assembly, part number 1-170-240-93, are producing fuel pressure, and,
if necessary, replacing the fuel regulator assembly with a serviceable
part. That AD was the result of a report of an accident involving a
T5317A-1 turboshaft engine installed on a Kaman Aerospace model K-1200
helicopter engaged in logging operations. That condition, if not
corrected, could result in engine failure and forced autorotation
landing.
Actions Since AD 98-22-11 Was Issued
Since we issued that AD, we received in 2004 a report of an engine
failure in a single-engine helicopter, which led to a forced
autorotation landing. Investigation revealed that excessive wear of the
fuel control regulator assembly pump splines caused the power loss. We
also became aware of reports of abnormally excessive wear of fuel
control regulator pump assembly pump splines. These parts are installed
in Goodrich Pump & Engine Control Systems, Inc. (GPECS) (formerly
Chandler Evans Control Systems) engine fuel control regulator assembly
models TA-2S, TA-2G, TA-2F, TA-7, and TA-10. These fuel control
regulator assembly models are installed on T5311A, T5311B, T5313B,
T5317A, T5317A-1, T5317B, T53-L-11B, T53-L-11D, T53-L-13B, T53-L-13B/D,
and T53-L-703 series turboshaft engines. This condition, if not
corrected, could result in an in-flight engine failure and forced
autorotation landing.
Relevant Service Information
We have reviewed and approved the technical contents of GPECS (TA
series) Service Bulletin (SB) No. 73-42, Revision 1, dated August 12,
2004. That SB describes procedures for performing visual and
dimensional inspections of the fuel control regulator assembly pump
splines.
Differences Between the Proposed AD and the Manufacturer's Service
Information
Although the SB recommends return of the entire fuel control
regulator assembly to GPECS if the pump spline wear is not within
limits, this proposed AD does not require that.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. We are proposing this AD, which would require
initial and repetitive visual and dimensional inspections of the fuel
control regulator pump assembly pump splines of GPECS engine fuel
controls models TA-2S, TA-2G, TA-2F, TA-7, and TA-10. The proposed AD
would require you to use the service information described previously
to perform these actions.
Costs of Compliance
There are about 700 Honeywell International Inc., T5311A, T5311B,
T5313B, T5317A, T5317A-1, and T5317B series turboshaft engines and
Lycoming former military T53-L-11B, T53-L-11D, T53-L-13B, T53-L-13B/D,
and T53-L-703 series turboshaft engines of the affected design in the
worldwide fleet. We estimate that this proposed AD would affect 592
engines installed on helicopters of U.S. registry. We also estimate
that it would take about 8 work hours per engine to perform an
inspection, and that the average labor rate is $65 per work hour. Based
on these figures, we estimate the cost of the proposed AD to U.S.
operators for one inspection to be $307,840. A replacement fuel control
regulator pump assembly would cost about $18,000. We estimate that if
all affected fuel control regulator pump assemblies failed inspection
and had to be replaced, the total parts cost of the proposed AD to U.S.
operators would be $10,656,000.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify that the proposed
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. Would 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 proposal and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 98-ANE-72-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 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. The FAA amends Sec. 39.13 by removing Amendment 63 FR 66741
(December 3, 1998) airworthiness directive to read as follows:
Honeywell International Inc.: Docket No. 98-ANE-72-AD.
[[Page 77075]]
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by February 27,
2006.
Affected ADs
(b) This AD supersedes AD 98-22-11, Amendment 39-10926.
Applicability
(c) This AD applies to Honeywell International Inc., (formerly
AlliedSignal, Inc., formerly Textron Lycoming, formerly Avco
Lycoming) T5311A, T5311B, T5313B, T5317A, T5317A-1, and T5317B
series turboshaft engines and Lycoming former military T53-L-11B,
T53-L-11D, T53-L-13B, T53-L-13B/D, and T53-L-703 series turboshaft
engines using Goodrich Pump & Engine Control Systems, Inc. (GPECS)
(formerly Chandler Evans Control Systems) engine fuel control
regulator assembly models TA-2S, TA-2G, TA-2F, TA-7, or TA-10.
(d) The T5311A, T5311B, T5313B, T5317A, T5317A-1, and T5317B
turboshaft engines are installed on, but not limited to, Bell 204,
205, and Kaman K-1200 helicopters. Lycoming T53-L-11B, T53-L-11D,
T53-L-13B, T53-L-13B/D, and T53-L-703 series turboshaft engines are
installed on, but not limited to, Bell AH-1 and UH-1 helicopters
certified under Sec. 21.25 or 21.27 of the Code of Federal
Regulations (14 CFR 21.25 or 14 CFR 21.27).
Unsafe Condition
(e) This AD results from several reports of loss of fuel flow
from the engine fuel control regulator assembly due to failure of
both main and secondary drive shaft and pump gear splines. We are
issuing this AD to prevent in-flight engine failure and forced
autorotation landing.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
Initial Visual and Dimensional Inspection
(g) Within 150 flight hours after the effective date of this AD,
do the following:
(1) Remove the fuel control regulator assembly from the engine
and perform an initial visual and dimensional inspection of the fuel
control regulator assembly main and secondary drive shaft and pump
gear splines for wear.
(2) Use paragraphs 2.A. through 2.D.(7) and 2.E. through 2.F.(2)
of the Accomplishment Instructions of Goodrich Pump & Engine Control
Systems, Inc. (TA series) Service Bulletin (SB) No. 73-42, Revision
1, dated August 12, 2004 to do the inspection.
(3) Do not install any engine fuel control regulator assembly
that fails inspection.
Repetitive Visual and Dimensional Inspections
(h) Thereafter, within every 1, 250 flight hours since-last-
inspection, perform repetitive visual and dimensional inspections of
the fuel control regulator assembly main and secondary drive shaft
and pump gear splines for wear, as specified in paragraphs (g)(1)
through (g)(3) of this AD.
Alternative Methods of Compliance
(i) The Manager, Los Angeles 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
(j) Honeywell International Inc. Service Bulletin No. T53-0138,
Revision 1, dated May 5, 2005, also pertains to the subject of this
AD, and is an FAA-approved alternative method of compliance for AD
98-22-11.
Issued in Burlington, Massachusetts, on December 22, 2005.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E5-8019 Filed 12-28-05; 8:45 am]
BILLING CODE 4910-13-P