[Federal Register: December 14, 2004 (Volume 69, Number 239)]
[Rules and Regulations]
[Page 74411-74412]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14de04-4]
[[Page 74411]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NE-09-AD; Amendment 39-13906; AD 2004-25-18]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney Canada PT6A-60A and
PT6A-65B Turboprop Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Pratt & Whitney Canada (PWC) PT6A-60A and PT6A-65B turboprop engines.
This AD requires replacing Woodward propeller governor assemblies, part
number (P/N) 8210-212H. This AD results from six incidents during
airplane acceptance flight testing where directional control of the
airplane was difficult to maintain during landing. We are issuing this
AD to prevent loss of directional control and damage to the airplane.
DATES: This AD becomes effective January 18, 2005.
ADDRESSES: You can get the service information identified in this AD
from Pratt & Whitney Canada, 1000 Marie-Victorin, Longueuil, Quebec,
Canada J4G1A1.
You may examine the AD docket, by appointment, at the FAA, New
England Region, Office of the Regional Counsel, 12 New England
Executive Park, Burlington, MA.
FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7178; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed airworthiness directive (AD). The proposed AD applies
to PWC PT6A-60A and PT6A-65B turboprop engines. We published the
proposed AD in the Federal Register on June 17, 2003, (68 FR 35826).
That action proposed to require replacing Woodward propeller governor
assemblies, P/N 8210-212H.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Suggestion That the Solenoid-Actuated Design Is Not Hazardous
One commenter suggests that the solenoid-actuated design is not
considered hazardous and will not cause ``total'' loss of directional
control. The commenter admits that this condition will affect
directional control but states, based on Raytheon Aircraft Company
flight tests with one solenoid failed during certification, ``at no
time was directional control totally lost or any damage incurred to the
aircraft.''
We do not agree. Although Raytheon Aircraft Company conducted a
flight test that did not result in ``total'' loss of control or damage
to the airplane, we feel the test was flown under more controlled
circumstances than those occurring in service and with knowledge that
one solenoid was failed during the test. The commenter doesn't address
the situation where an average pilot, experiencing this failure
unexpectedly, would make the correct control responses at the correct
times to prevent ``total'' loss of directional control and damage to
the aircraft. We have not changed the AD.
Request To Add Models PT6A-60AG, PT6A-65AR, and PT6A-65R to the
Applicability
The same commenter asks us to add PWC models PT6A-60AG, PT6A-65AR,
and PT6A-65R to the applicability of the AD. The commenter points to
the discrepancy in engine models between the proposed AD and the PWC
Service Bulletin (SB) PT6A-72-13354, dated July 6, 2001.
We do not agree. Although the SB addresses both propeller governor
configurations, this AD only addresses those propeller governors, P/N
8210-212H, that connect to a solenoid valve installed on an airplane.
The engine models PT6A-60A and PT6A-65B are installed on airplanes
operating with a solenoid valve. The other engine models, incorporating
Woodward Propeller Governor, P/N 8210-212J, are installed on airplanes
configured with a push-pull rod mechanism. These engine models are not
affected by this AD. We have not changed the AD.
Request To Write the AD Against the Propeller Governor Rather Than the
Engine
One commenter requests that the AD be written against the propeller
governor rather than the engine. The commenter states that there is
nothing wrong with the engine except when it is used with a particular
propeller governor.
We do not agree. Even though there is nothing wrong with either the
propeller governor or the engine if isolated from the aircraft system,
the propeller governor design is compromised when it operates on
aircraft configured with a solenoid valve. Therefore, the combined
system level interaction between an aircraft level component (solenoid
valve) and the engine level part (propeller governor) makes this AD
action necessary. We have not changed the AD.
Request To Include Additional Aircraft to the Applicability
One commenter requests that both the Air Tractor AT-802A and the
CASA C-212-DE aircraft be included in the applicability. The commenter
states that the PT6A-65B engine model is installed on these aircraft.
We do not agree. While PT6A-65B engines are installed on these
airplanes, the airplanes have a push-pull rod activation mechanism.
This AD does not affect those engines. We have not changed the AD.
Revision 1 to PWC SB PT6A-72-13354
After we issued the NPRM, we learned that PWC issued P&WC SB No.
PT6A-72-13354, Revision 1, dated July 11, 2003. This SB calls out
certain PT6A-60 and PT6A-65B engines by engine serial number. We added
the affected engine serial numbers to the applicability section of this
AD, and changed the reference to the SB in compliance paragraph (f) to
P&WC SB No. PT6A-72-13354, Revision 1, dated July 11, 2003.
Increased Labor Rate in the Costs of Compliance
After we issued the NPRM, the Office of Aviation Policy and Plans
changed the average labor rate in the Costs of Compliance from $60.00
to $65.00. We changed the labor rate in the Costs of Compliance to
$65.00 and adjusted the total cost to operators.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
Costs of Compliance
There are about 73 PWC PT6A-60A and PT6A-65B turboprop engines of
the affected design in the worldwide fleet. We estimate that 70 engines
installed on airplanes of U.S. registry will be affected by this AD. We
also estimate that it will take about 2 work hours per engine to
perform the actions, and that the average labor rate is $65 per work
hour.
[[Page 74412]]
Required parts would cost approximately $24,228 per engine. Based on
these figures, we estimate the total cost of the AD to U.S. operators
to be $1,705,060. The manufacturer informed us that it might provide
the parts and labor to the operators at no cost, substantially reducing
the cost impact of this rule.
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 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. 2003-NE-09-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, 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 adding the following new airworthiness
directive (AD):
2004-25-18 Pratt & Whitney Canada: Amendment 39-13906. Docket No.
2003-NE-09-AD.
Effective Date
(a) This AD becomes effective January 18, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Pratt & Whitney Canada (PWC) PT6A-60A
turboprop engines, with an engine serial number (SN) which is before
and includes SN PCE-PK0425, and SNs PCE-95006 thru PCE-95828, and
PT6A-65B turboprop engines, with a SN which is before and includes
SN PCE-PP0062, and PCE-32001 thru PCE-32644 and all engines
converted to engine model PT6A-65B, that have Woodward propeller
governor assemblies, part number (P/N) 8210-212H, installed. These
engines are installed on, but not limited to, Raytheon Super Beech
King Air 300/350 and Raytheon Beech 1900/1900C airplanes.
Unsafe Condition
(d) This AD results from six incidents during airplane
acceptance flight testing, whereby directional control of the
airplane was difficult to maintain during landing. The actions
specified in this AD are intended to prevent loss of directional
control and damage to the airplane.
Compliance
(e) Compliance with this AD is required as indicated, unless
already done.
Removal of Woodward Propeller Governor Assemblies
(f) Replace Woodward propeller governor assemblies, P/N 8210-
212H, at the next access to the governor or within six months after
the effective date of this AD, whichever occurs earlier. Information
on replacing the Woodward propeller governor assembly can be found
in Pratt & Whitney Canada Service Bulletin No. PT6A-72-13354,
Revision 1, dated July 11, 2003.
(g) After the effective date of this AD, do not install any
Woodward propeller governor assembly, P/N 8210-212H, on any engine.
Alternative Methods of Compliance
(h) The Manager, Engine 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
(i) The subject of this AD is addressed in Transport Canada
airworthiness directive CF-2002-02, dated January 15, 2002.
Material Incorporated by Reference
(j) None.
Issued in Burlington, Massachusetts, on December 6, 2004.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 04-27319 Filed 12-13-04; 8:45 am]
BILLING CODE 4910-13-P