[Federal Register Volume 71, Number 104 (Wednesday, May 31, 2006)]
[Rules and Regulations]
[Pages 30795-30796]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-4908]



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 Rules and Regulations
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  Federal Register / Vol. 71, No. 104 / Wednesday, May 31, 2006 / Rules 
and Regulations  

[[Page 30795]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-72-AD; Amendment 39-14620; AD 2006-11-16]
RIN 2120-AA64


Airworthiness Directives; 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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) 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 AD requires 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 AD also expands the engine 
applicability, and includes 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 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.

DATES: This AD becomes effective July 5, 2006. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of July 5, 2006.

ADDRESSES: You can get the service information identified in this AD 
from Goodrich Pumps & Engine Control Systems, P.O. Box 3306519, West 
Hartford, CT 06133, fax (860) 231-2718.
    You may examine the AD docket at the FAA, New England Region, 
Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA. You may examine the service information, 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: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to 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. We 
published the proposed AD in the Federal Register on December 28, 2005 
(70 FR 77073). That action proposed to 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. That action also proposed to 
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).

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.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the one comment received.
    The commenter, Honeywell International Inc., states that they 
issued or revised three service bulletins in response to the unsafe 
condition in the proposed AD. We note that they have issued the service 
bulletins. We did not change the AD based on this comment.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD as proposed.

Costs of Compliance

    We estimate that this AD will affect 592 engines installed on 
helicopters of U.S. registry. We also estimate that it will take about 
8 workhours 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 AD to U.S. operators for one inspection to be $307,840. 
A replacement fuel control regulator pump assembly will 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 AD to U.S. operators will 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.

[[Page 30796]]

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will 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 this AD:
    (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.
    We prepared a summary of the costs to comply with this AD 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 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. The FAA amends Sec.  39.13 by removing Amendment 39-10926 (63 FR 
66741, December 3, 1998) and by adding a new airworthiness directive, 
Amendment 39-14620, to read as follows:

2006-11-16 Honeywell International Inc. (formerly AlliedSignal, 
Inc., formerly Textron Lycoming, formerly Avco Lycoming): Amendment 
39-14620. Docket No. 98-ANE-72-AD.

Effective Date

    (a) This AD becomes effective July 5, 2006.

Affected ADs

    (b) This AD supersedes AD 98-22-11.

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.

Material Incorporated by Reference

    (k) You must use Goodrich Pump & Engine Control Systems, Inc. 
(TA series) Service Bulletin (SB) No. 73-42, Revision 1, dated 
August 12, 2004, to perform the inspections required by this AD. The 
Director of the Federal Register approved the incorporation by 
reference of this service bulletin in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. You can get a copy from Goodrich Pumps & 
Engine Control Systems, P.O. Box 3306519, West Hartford, CT 06133, 
fax (860) 231-2718. You can review a copy at the FAA, New England 
Region, Office of the Regional Counsel, 12 New England Executive 
Park, Burlington, MA; or at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on May 23, 2006.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 06-4908 Filed 5-30-06; 8:45 am]
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