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[Federal Register: November 24, 2008 (Volume 73, Number 227)] 

[Rules and Regulations] 

[Page 70866-70867] 

From the Federal Register Online via GPO Access [wais.access.gpo.gov] 

[DOCID:fr24no08-2] 

–––––––––––––––––––––––––––––––––– 

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. 

–––––––––––––––––––––––––––––––––– 

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. 
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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 singleengine 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. 
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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-CE070-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, ''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. 
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Adoption of the Amendment 

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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 adding the following new airworthiness directive (AD): 
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FAA 

Aircraft Certification Service

AIRWORTHINESS DIRECTIVE

www.faa.gov/aircraft/safety/alerts/ 

www.gpoaccess.gov/fr/advanced.html

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 
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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.