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, 77073-77075 [E5-8019]

Download as PDF Federal Register / Vol. 70, No. 249 / Thursday, December 29, 2005 / Proposed Rules pertinent to GPEA compliance related to this proposed rule, please contact Mrs. Celeste Sickles, APHIS’ Information Collection Coordinator, at (301) 734– 7477. List of Subjects in 7 CFR Part 319 Coffee, Cotton, Fruits, Imports, Logs, Nursery stock, Plant diseases and pests, Quarantine, Reporting and recordkeeping requirements, Rice, Vegetables. Accordingly, we propose to amend 7 CFR part 319 as follows: PART 319—FOREIGN QUARANTINE NOTICES 1. The authority citation for part 319 would continue to read as follows: Authority: 7 U.S.C. 450, 7701–7772, and 7781–7786; 21 U.S.C. 136 and 136a; 7 CFR 2.22, 2.80, and 371.3. 2. A new § 319.56–2oo would be added to read as follows: safeguards must remain intact until the arrival of the peppers in the United States or the shipment will not be allowed to enter the United States. (e) Each shipment of peppers must be accompanied by a phytosanitary certificate of inspection issued by NPQS bearing the following additional declaration: ‘‘These peppers were grown in greenhouses in accordance with the conditions in 7 CFR 319.56–2oo and were inspected and found free from Agrotis segetum, Helicoverpa armigera, Helicoverpa assulta, Mamestra brassicae, Monilinia fructigena, Ostrinia furnacalis, Scirtothrips dorsalis, Spodoptera litura, and Thrips palmi.’’ (f) The peppers must be imported in commercial shipments only. Done in Washington, DC, this 21st day of December 2005. Nick Gutierrez, Acting Administrator, Animal and Plant Health Inspection Service. [FR Doc. E5–8028 Filed 12–28–05; 8:45 am] wwhite on PROD1PC65 with PROPOSAL § 319.56–2oo Administrative instructions; conditions governing the entry of peppers from the Republic of Korea. BILLING CODE 3410–34–P Peppers (Capsicum annuum L. Var. annuum) from the Republic of Korea may be imported into the continental United States only under the following conditions: (a) The peppers must be grown in the Republic of Korea in insect-proof greenhouses approved by and registered with the National Plant Quarantine Service (NPQS). (b) The greenhouses must be equipped with double self-closing doors, and any vents or openings in the greenhouses (other than the double selfclosing doors) must be covered with 0.6 mm screening in order to prevent the entry of pests into the greenhouse. (c) The greenhouses must be inspected monthly throughout the growing season by NPQS to ensure phytosanitary procedures are employed to exclude plant pests and diseases, and that the screens are intact. (d) The peppers must be packed within 24 hours of harvest in a pest exclusionary packinghouse. During the time the packinghouse is in use for exporting peppers to the continental United States, the packinghouse can accept peppers only from registered approved production sites. The peppers must be safeguarded by an insect-proof mesh screen or plastic tarpaulin while in transit from the production site to the packinghouse and while awaiting packing. The peppers must be packed in insect-proof cartons or containers, or covered with insect-proof mesh or plastic tarpaulin, for transit to the continental United States. These DEPARTMENT OF TRANSPORTATION VerDate Aug<31>2005 16:10 Dec 28, 2005 Jkt 208001 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 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 77073 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 § 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-aneadcomment@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 datestamp 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 E:\FR\FM\29DEP1.SGM 29DEP1 77074 Federal Register / Vol. 70, No. 249 / Thursday, December 29, 2005 / Proposed Rules 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. wwhite on PROD1PC65 with PROPOSAL 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 VerDate Aug<31>2005 16:10 Dec 28, 2005 Jkt 208001 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, PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 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. § 39.13 [Amended] 2. The FAA amends § 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. E:\FR\FM\29DEP1.SGM 29DEP1 Federal Register / Vol. 70, No. 249 / Thursday, December 29, 2005 / Proposed Rules splines for wear, as specified in paragraphs (g)(1) through (g)(3) of this AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by February 27, 2006. 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. 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 § 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. wwhite on PROD1PC65 with PROPOSAL 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 VerDate Aug<31>2005 16:10 Dec 28, 2005 Jkt 208001 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 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 97–ANE–44–AD] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney PW4164, PW4168, and PW4168A Series Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) for Pratt & Whitney (PW) PW4164, PW4168, and PW4168A series turbofan engines. That AD currently requires initial and repetitive torque checks for loose or broken front pylon mount bolts made from INCO 718 material and MP159 material, and initial and repetitive visual inspections of the primary mount thrust load path. This proposed AD would require the same actions, but at reduced intervals for front pylon mount bolts made from MP159 material. This proposed AD results from analysis by the manufacturer that the MP159 material pylon bolts do not meet the full life cycle torque check interval requirement, in a bolt-out condition. We are proposing this AD to prevent front pylon mount bolt and primary mount thrust load path failure, which could result in an engine separating from the airplane. DATES: We must receive any comments on this proposed AD by February 27, 2006. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 77075 Use one of the following addresses to submit comments on this proposed AD: • By mail: Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 97–ANE– 44–AD, 12 New England Executive Park, Burlington, MA 01803–5299. • By fax: (781) 238–7055. • By e-mail: 9-aneadcomment@faa.gov. Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565–7700, fax (860) 565–1605 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: Barbara Caufield, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803–5299; telephone (781) 238–7146, fax (781) 238–7199. SUPPLEMENTARY INFORMATION: ADDRESSES: Comments Invited We invite you to submit any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘AD Docket No. 97– ANE–44–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 datestamp 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 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 December 19, 2002, we issued AD 2000–16–02R1, Amendment 39–12989 (68 FR 28, January 2, 2003). That AD requires initial and repetitive torque E:\FR\FM\29DEP1.SGM 29DEP1

Agencies

[Federal Register Volume 70, Number 249 (Thursday, December 29, 2005)]
[Proposed Rules]
[Pages 77073-77075]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E5-8019]


=======================================================================
-----------------------------------------------------------------------

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).

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

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

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