[Federal Register Volume 73, Number 227 (Monday, November 24, 2008)]
[Rules and Regulations]
[Pages 70866-70867]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-27699]



[[Page 70866]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1232; Directorate Identifier 2008-CE-070-AD; 
Amendment 39-15747; AD 2008-24-07]
RIN 2120-AA64


Airworthiness Directives; Eclipse Aviation Corporation Model 
EA500 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Eclipse Aviation Corporation (Eclipse) Model EA500 airplanes 
equipped with a Pratt and Whitney Canada, Corp. (PWC) PW610F-A engine. 
This AD requires you to incorporate operating limitations into Section 
2, Limitations, of the airplane flight manual (AFM). This AD results 
from several incidents of engine surge. We are issuing this AD to 
prevent hard carbon buildup on the static vane, which could result in 
engine surges. Engine surges may result in a necessary reduction in 
thrust and decreased power for the affected engine. In some cases, this 
could result in flight and landing under single-engine conditions.

DATES: This AD becomes effective on December 4, 2008.
    We must receive any comments on this AD by January 23, 2009.

ADDRESSES: Use one of the following addresses to comment on this AD.
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    To view the comments to this AD, go to http://www.regulations.gov. 
The docket number is FAA-2008-1232; Directorate Identifier 2008-CE-070-
AD.

FOR FURTHER INFORMATION CONTACT: Mitchell Soth, Flight Test Engineer, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222-5104; 
fax: (817) 222-5960.

SUPPLEMENTARY INFORMATION:

Discussion

    While in cruising flight at 40,000 feet altitude, an Eclipse EA500 
airplane experienced a shudder from the right engine. This was followed 
by a ``RT ENGINE EXCEEDANCE'' Crew Alerting System (CAS) message. The 
crew reduced the throttle to idle and the shudder disappeared. The 
right engine remained at idle until approximately 10,000 feet altitude. 
The crew increased the power on the right engine and again felt the 
shudder. The crew reduced the power on the right engine to idle and 
landed without incident using single-engine procedures. PWC did a 
borescope inspection and found carbon buildup on the static vane, which 
caused the engine surging.
    When the PW610F-A engine is operated above 37,000 feet altitude, 
for over an hour, and with high bleed flow, hard carbon forms due to 
high local fuel air ratio near the combustor wall. The hard carbon may 
break loose and obstruct one of the high pressure turbine vane gas path 
passages, thus decreasing the surge margin to the point where engine 
surging occurs.
    There have been several reports of engine surges that have required 
reduced power, and, in some cases, the engine power was unrecoverable 
and remained at reduced power for the remainder of the flight.
    This condition, if not corrected, could result in hard carbon 
buildup on the static vane, which could result in engine surges. Engine 
surges may result in a necessary reduction in thrust and decreased 
power for the affected engine. In some cases, this could result in 
flight and landing under single-engine conditions.

FAA's Determination and Requirements of This AD

    We are issuing this AD because we evaluated all the information and 
determined the unsafe condition described previously is likely to exist 
or develop on other products of the same type design. This AD requires 
you to incorporate operating limitations into Section 2, Limitations, 
of the AFM.
    The PW610F-A engines are currently only installed in the Eclipse 
Model EA500 airplanes. If these engines were installed in other 
airplanes, we would consider immediate AD action on those airplanes 
since the engine would be of the same type design and the unsafe 
condition could exist or develop in products of the same type design.
    The FAA considers the altitude limitation to be interim action. The 
PWC PW610F-A engine is certificated in Canada and is certificated as a 
foreign type validated engine under FAA TCDS E00074EN. The FAA 
understands that Transport Canada (the airworthiness authority for 
Canada) and PWC are considering potential actions to address the engine 
aspects of this condition. In the meantime, the FAA is issuing this AD 
on the Eclipse Model EA500 to mandate an altitude limitation.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because hard 
carbon buildup on the static vane could result in engine surges. Engine 
surges may require decreased power for the affected engine and, in some 
cases, flight and landing under single-engine conditions. Therefore, we 
determined that notice and opportunity for public comment before 
issuing this AD are impracticable and that good cause exists for making 
this amendment effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and an opportunity for 
public comment. We invite you to send any written relevant data, views, 
or arguments regarding this AD. Send your comments to an address listed 
under the ADDRESSES section. Include the docket number ``FAA-2008-1232; 
Directorate Identifier 2008-CE-070-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the AD in light 
of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive concerning this AD.

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,

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``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 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 regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket that contains the AD, the regulatory 
evaluation, any comments received, and other information on the 
Internet at http://www.regulations.gov; or in person at the Docket 
Management Facility between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Office (telephone (800) 647-5527) 
is located at the street address stated in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

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 FAA 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):

2008-24-07 Eclipse Aviation Corporation: Amendment 39-15747; Docket 
No. FAA-2008-1232; Directorate Identifier 2008-CE-070-AD.

Effective Date

    (a) This AD becomes effective on December 4, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model EA500 airplanes, all serial 
numbers, that are:
    (1) Equipped with a Pratt and Whitney Canada, Corp. PW610F-A 
engine; and
    (2) Certificated in any category.

Unsafe Condition

    (d) This AD is the result of several incidents of engine surge. 
We are issuing this AD to prevent hard carbon buildup on the static 
vane, which could result in engine surges. Engine surges may result 
in a necessary reduction in thrust and decreased power for the 
affected engine. In some cases, this could result in flight and 
landing under single-engine conditions.

Compliance

    (e) Prior to further flight, unless already done, incorporate 
the following language into Section 2, Limitations, of your airplane 
flight manual (AFM): ``Per AD 2008-24-07, LIMIT THE MAXIMUM 
OPERATING ALTITUDE TO 37,000 FEET (11277M) PRESSURE ALTITUDE.''
    (1) A person holding at least a private pilot certificate as 
authorized by section 43.7 of the Federal Aviation Regulations (14 
CFR 43.7) may insert the operating limitations into Section 2, 
Limitations, of the AFM. Make an entry into the aircraft logbook 
showing compliance with this portion of the AD in accordance with 
section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).
    (2) You may incorporate paragraph (e) of this AD into Section 2, 
Limitations, of your AFM to comply with this AD.

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Fort Worth Airplane Certification Office, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. Send information to Attn: 
Mitchell Soth, Aerospace Engineer, 2601 Meacham Blvd., Fort Worth, 
Texas 76137; telephone: (817) 222-5104; fax: (817) 222-5960. Before 
using any approved AMOC on any airplane to which the AMOC applies, 
notify your appropriate principal inspector (PI) in the FAA Flight 
Standards District Office (FSDO), or lacking a PI, your local FSDO.

    Issued in Kansas City, Missouri, on November 17, 2008.
Kim Smith,
Manager Small Airplane Directorate, Aircraft Certification Service.
 [FR Doc. E8-27699 Filed 11-21-08; 8:45 am]
BILLING CODE 4910-13-P