Airworthiness Directives; Pratt & Whitney Canada PT6A-60A and PT6A-65B Turboprop Engines

[Federal Register Volume 69, Number 239 (Tuesday, December 14, 2004)]
[Rules and Regulations]
[Pages 74411-74412]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-27319]



[[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

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