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 

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 

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. 

Examining the AD Docket 

You may examine the AD docket 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 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 inflight 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 


jdjones on DSK8KYBLC1PROD with RULES
Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations 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 http:// 

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 Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

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.

Not Applicable ................. $85 $22,015 

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 

■ 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 

(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 


jdjones on DSK8KYBLC1PROD with RULES
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. 

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 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0154; Directorate 

Identifier 2011–NM–016–AD; Amendment 

39–16624; AD 2011–05–14] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8–400 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: 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: 

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. 

DATES: 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 

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 W12–40, 1200 New Jersey 

Avenue, SE., Washington, DC, 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 http:// 

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: 

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 

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 


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