Airworthiness Directives; Eclipse Aerospace, Inc. Model EA500 Airplanes Equipped With a Pratt and Whitney Canada, Corp. (PWC) PW610F-A Engine, 13078-13080 [2011-5296]

Download as PDF 13078 Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations Material Incorporated by Reference (k) None. Issued in Renton, Washington, on February 28, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–5293 Filed 3–9–11; 8:45 am] BILLING CODE 4910–13–P 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. Examining the AD Docket DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0199; Directorate Identifier 2011–CE–005–AD; Amendment 39–16631; AD 2011–06–06] RIN 2120–AA64 Airworthiness Directives; Eclipse Aerospace, Inc. Model EA500 Airplanes Equipped With a Pratt and Whitney Canada, Corp. (PWC) PW610F–A Engine Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are superseding an existing airworthiness directive (AD) for the products listed above. That AD currently requires you to incorporate operating limitations of maximum operating altitude of 37,000 feet into Section 2, Limitations, of the airplane flight manual (AFM). This AD requires you to incorporate operating limitations of maximum operating altitude of 30,000 feet into Section 2, Limitations, of the AFM. This AD was prompted by 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. It is also possible this could affect both engines at the same time, requiring dual-engine shutdown. DATES: This AD is effective March 21, 2011. We must receive any comments on this AD by April 25, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, jdjones on DSK8KYBLC1PROD with RULES SUMMARY: VerDate Mar<15>2010 14:45 Mar 09, 2011 Jkt 223001 You may examine the AD docket on the Internet at https:// 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 AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Eric Kinney, Aerospace Engineer, Ft. Worth Aircraft Certification Office, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222–5459; fax: (817) 222–5960; e-mail: eric.kinney@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On November 17, 2008, we issued AD 2008–24–07, amendment 39–15747 (73 FR 70866, November 24, 2008), for certain Eclipse Aviation Corporation (Eclipse) Model EA500 airplanes equipped with a Pratt and Whitney Canada, Corp. (PWC) PW610F–A engine. That AD requires you to incorporate operating limitations into Section 2, Limitations, of the airplane flight manual (AFM). That AD resulted from several incidents of engine surge. We issued that 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. flight shutdown of the affected engine. This could occur in flight and require landing under single-engine conditions. It is also possible that this could affect both engines at the same time, requiring dual-engine shutdown. FAA’s Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. AD Requirements This AD requires you to incorporate operating limitations of maximum operating altitude of 30,000 feet into Section 2, Limitations, of the AFM. Interim Action We consider this AD 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 address the immediate unsafe condition and to mandate the altitude limitation. Actions Since AD was Issued FAA’s Justification and 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 a reduction of available thrust or an in-flight shutdown of the affected engine might occur. This could occur in flight and require landing under single-engine conditions. It is also possible that this could affect both engines at the same time, requiring dual-engine shutdown. Therefore, we find that notice and opportunity for prior public comment are impracticable and that good cause exists for making this amendment effective in less than 30 days. Since we issued AD 2008–24–07, the unsafe condition of engine surges due to hard carbon build up blocking the static vanes has continued to occur at 37,000 feet altitude and lower. Six known events have occurred, five of which were at or below 37,000 feet altitude and four of which were in a two-week period. Operating effects may include a reduction of available thrust or an in- Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 E:\FR\FM\10MRR1.SGM 10MRR1 13079 Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations FAA–2011–0199 and directorate identifier 2011–CE–005–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance We estimate that this AD affects 259 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Parts cost Cost per product Cost on U.S. operators Not Applicable ................. $85 $22,015 Labor cost Incorporate operating limitations of maximum operating altitude of 30,000 feet into Section 2, Limitations, of the AFM. 1 work-hour × $85 per hour = $85. (3) Will not affect intrastate aviation in Alaska, and (4) 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. 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. jdjones on DSK8KYBLC1PROD with RULES The cost presented above is a cost estimate only. Since 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 AFM change, the cost burden of this AD on the individual owner/operator is minimal or nothing. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Regulatory Findings 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), VerDate Mar<15>2010 14:45 Mar 09, 2011 Jkt 223001 List of Subjects in 14 CFR Part 39 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends part 39 of the Federal Aviation Regulations (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 removing airworthiness directive (AD) 2008–24–07, Amendment 39–15747 (73 FR 70866, November 24, 2008) and adding the following new AD: ■ 2011–06–06 Eclipse Aerospace, Inc. Model EA500 Airplanes Equipped With a Pratt and Whitney Canada, Corp. (PWC) PW610F–A Engine: Amendment 39– 16631; Docket No. FAA–2011–0199; Directorate Identifier 2011–CE–005–AD. Effective Date (a) This AD is effective March 21, 2011. Affected ADs (b) This AD supersedes AD 2008–24–07, Amendment 39–15747. 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 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 (2) certificated in any category. Subject (d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 72, Engine. Unsafe Condition (e) This AD was prompted by 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. It is also possible this could affect both engines at the same time, requiring dual-engine shutdown. Compliance (f) Comply with this AD within the compliance times specified, unless already done. Actions (g) Before further flight, incorporate the following language into Section 2, Limitations, of your airplane flight manual (AFM): ‘‘Per AD 2011–06–06, LIMIT THE MAXIMUM OPERATING ALTITUDE TO 30,000 FEET (9144M) 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 (g) of this AD into Section 2, Limitations, of your AFM to comply with this AD. Alternative Methods of Compliance (AMOCs) (h)(1) 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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly E:\FR\FM\10MRR1.SGM 10MRR1 13080 Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. Federal Aviation Administration This AD becomes effective March 25, 2011. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of March 25, 2011. We must receive comments on this AD by April 25, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://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 W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2011–0154; Directorate Identifier 2011–NM–016–AD; Amendment 39–16624; AD 2011–05–14] You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Fabio Buttitta, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228– 7303; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: Related Information (i) For more information about this AD, contact Eric Kinney, Aerospace Engineer, Ft. Worth Aircraft Certification Office, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222–5459; fax: (817) 222–5960; e-mail: eric.kinney@faa.gov. Issued in Kansas City, Missouri, on March 3, 2011. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–5296 Filed 3–9–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Model DHC–8–400 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: jdjones on DSK8KYBLC1PROD with RULES SUMMARY: Two cases of the main landing gear (MLG) alternate extension system (AES) cam mechanism failure were found during line checks. The cam mechanism operates the cable to open the MLG door and releases the MLG uplock in sequence. In the case where it is necessary to deploy the MLG using the AES, the failure of the MLG AES cam mechanism on one side will lead to an unsafe asymmetrical landing configuration. * * * * * The unsafe condition is possible loss of control during landing. This AD requires actions that are intended to address the unsafe condition described in the MCAI. VerDate Mar<15>2010 14:45 Mar 09, 2011 Jkt 223001 DATES: Discussion The Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Emergency Airworthiness Directive CF– 2011–01, dated January 17, 2011 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Two cases of the main landing gear (MLG) alternate extension system (AES) cam mechanism failure were found during line checks. The cam mechanism operates the cable to open the MLG door and releases the MLG uplock in sequence. In the case where it is necessary to deploy the MLG using the AES, the failure of the MLG AES cam PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 mechanism on one side will lead to an unsafe asymmetrical landing configuration. Preliminary investigation indicates that the cam mechanism failure may have occurred and remained dormant after a previous AES operation. The cam mechanism may not have fully returned to the normal rested position. With the cam mechanism out of normal rested position, normal powered landing gear door operation could introduce sufficient loads to fracture the cam mechanism or rupture the door release cable. This directive mandates the initial and subsequent [detailed] inspections for proper operation of the MLG AES cam mechanism, and rectify [repair or replace cam assembly with new or serviceable cam assembly] as necessary. The unsafe condition is possible loss of control during landing. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Bombardier has issued Repair Drawing 8/4–32–0160, Issue 2, dated January 18, 2011. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between the AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a Note within the AD. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this E:\FR\FM\10MRR1.SGM 10MRR1

Agencies

[Federal Register Volume 76, Number 47 (Thursday, March 10, 2011)]
[Rules and Regulations]
[Pages 13078-13080]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-5296]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0199; Directorate Identifier 2011-CE-005-AD; 
Amendment 39-16631; AD 2011-06-06]
RIN 2120-AA64


Airworthiness Directives; Eclipse Aerospace, Inc. Model EA500 
Airplanes Equipped With a Pratt and Whitney Canada, Corp. (PWC) PW610F-
A Engine

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for the products listed above. That AD currently requires you to 
incorporate operating limitations of maximum operating altitude of 
37,000 feet into Section 2, Limitations, of the airplane flight manual 
(AFM). This AD requires you to incorporate operating limitations of 
maximum operating altitude of 30,000 feet into Section 2, Limitations, 
of the AFM. This AD was prompted by 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. It is also possible this could affect both 
engines at the same time, requiring dual-engine shutdown.

DATES: This AD is effective March 21, 2011.
    We must receive any comments on this AD by April 25, 2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://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 AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Eric Kinney, Aerospace Engineer, Ft. 
Worth Aircraft Certification Office, FAA, 2601 Meacham Blvd., Fort 
Worth, Texas 76137; telephone: (817) 222-5459; fax: (817) 222-5960; e-
mail: eric.kinney@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    On November 17, 2008, we issued AD 2008-24-07, amendment 39-15747 
(73 FR 70866, November 24, 2008), for certain Eclipse Aviation 
Corporation (Eclipse) Model EA500 airplanes equipped with a Pratt and 
Whitney Canada, Corp. (PWC) PW610F-A engine. That AD requires you to 
incorporate operating limitations into Section 2, Limitations, of the 
airplane flight manual (AFM). That AD resulted from several incidents 
of engine surge. We issued that 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.

Actions Since AD was Issued

    Since we issued AD 2008-24-07, the unsafe condition of engine 
surges due to hard carbon build up blocking the static vanes has 
continued to occur at 37,000 feet altitude and lower.
    Six known events have occurred, five of which were at or below 
37,000 feet altitude and four of which were in a two-week period.
    Operating effects may include a reduction of available thrust or an 
in-flight shutdown of the affected engine. This could occur in flight 
and require landing under single-engine conditions. It is also possible 
that this could affect both engines at the same time, requiring dual-
engine shutdown.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

AD Requirements

    This AD requires you to incorporate operating limitations of 
maximum operating altitude of 30,000 feet into Section 2, Limitations, 
of the AFM.

Interim Action

    We consider this AD 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 
address the immediate unsafe condition and to mandate the altitude 
limitation.

FAA's Justification and 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 a 
reduction of available thrust or an in-flight shutdown of the affected 
engine might occur. This could occur in flight and require landing 
under single-engine conditions. It is also possible that this could 
affect both engines at the same time, requiring dual-engine shutdown. 
Therefore, we find that notice and opportunity for prior public comment 
are impracticable and that good cause exists for making this amendment 
effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
the docket number

[[Page 13079]]

FAA-2011-0199 and directorate identifier 2011-CE-005-AD at the 
beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
AD. We will consider all comments received by the closing date and may 
amend this AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 259 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
              Action                     Labor cost            Parts cost           product         operators
----------------------------------------------------------------------------------------------------------------
Incorporate operating limitations   1 work-hour x $85     Not Applicable......             $85          $22,015
 of maximum operating altitude of    per hour = $85.
 30,000 feet into Section 2,
 Limitations, of the AFM.
----------------------------------------------------------------------------------------------------------------

     The cost presented above is a cost estimate only. Since 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 
AFM change, the cost burden of this AD on the individual owner/operator 
is minimal or nothing.

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

    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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends part 39 of the Federal Aviation 
Regulations (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 airworthiness directive (AD) 
2008-24-07, Amendment 39-15747 (73 FR 70866, November 24, 2008) and 
adding the following new AD:

2011-06-06 Eclipse Aerospace, Inc. Model EA500 Airplanes Equipped 
With a Pratt and Whitney Canada, Corp. (PWC) PW610F-A Engine: 
Amendment 39-16631; Docket No. FAA-2011-0199; Directorate Identifier 
2011-CE-005-AD.

Effective Date

    (a) This AD is effective March 21, 2011.

Affected ADs

    (b) This AD supersedes AD 2008-24-07, Amendment 39-15747.

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.

Subject

    (d) Joint Aircraft System Component (JASC)/Air Transport 
Association (ATA) of America Code 72, Engine.

Unsafe Condition

    (e) This AD was prompted by 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. It is also possible this 
could affect both engines at the same time, requiring dual-engine 
shutdown.

Compliance

    (f) Comply with this AD within the compliance times specified, 
unless already done.

Actions

    (g) Before further flight, incorporate the following language 
into Section 2, Limitations, of your airplane flight manual (AFM): 
``Per AD 2011-06-06, LIMIT THE MAXIMUM OPERATING ALTITUDE TO 30,000 
FEET (9144M) 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 (g) of this AD into Section 2, 
Limitations, of your AFM to comply with this AD.

Alternative Methods of Compliance (AMOCs)

    (h)(1) 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. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly

[[Page 13080]]

to the manager of the ACO, send it to the attention of the person 
identified in the Related Information section of this AD.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

Related Information

    (i) For more information about this AD, contact Eric Kinney, 
Aerospace Engineer, Ft. Worth Aircraft Certification Office, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222-
5459; fax: (817) 222-5960; e-mail: eric.kinney@faa.gov.

    Issued in Kansas City, Missouri, on March 3, 2011.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011-5296 Filed 3-9-11; 8:45 am]
BILLING CODE 4910-13-P
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