Federal Register / Vol. 78, No. 33 / Tuesday, February 19, 2013 / Rules and Regulations 11563 

additional safety standards that the 

Administrator considers necessary to 

establish a level of safety equivalent to 

that established by the existing 

airworthiness standards. 

DATES: Effective date: March 21, 2013. 

FOR FURTHER INFORMATION CONTACT: Joe 

Jacobsen, FAA, Airplane and Flight 

Crew Interface Branch, ANM–111, 

Transport Airplane Directorate, Aircraft 

Certification Service, 1601 Lind Avenue 

SW., Renton, Washington 98057–3356; 

telephone 425–227–2011; facsimile 

425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Background 

On May 14, 2009, Embraer S.A. 

applied for a type certificate for their 

new Model EMB–550 airplane. The 

Model EMB–550 airplane is the first of 

a new family of jet airplanes designed 

for corporate flight, fractional, charter, 

and private owner operations. The 

aircraft has a conventional configuration 

with a low wing and T-tail empennage. 

The primary structure is metal with 

composite empennage and control 

surfaces. The Model EMB–550 airplane 

is designed for 8 passengers, with a 

maximum of 12 passengers. It is 

equipped with two Honeywell 

HTF7500–E medium bypass ratio 

turbofan engines mounted on aft 

fuselage pylons. Each engine produces 

approximately 6,540 pounds of thrust 

for normal takeoff. The primary flight 

controls consist of hydraulically 

powered fly-by-wire elevators, aileron 

and rudder, controlled by the pilot or 

copilot sidestick. 

The longitudinal control law design of 

the Embraer S.A. Model EMB–550 

airplane incorporates an overspeed 

protection system in the normal mode. 

This mode prevents the pilot from 

inadvertently or intentionally exceeding 

a speed approximately equivalent to VFC

or attaining VDF. Current Title 14, Code 

of Federal Regulations (14 CFR) part 25 

did not envision a high speed limiter 

that might preclude or modify flying 

qualities assessments in the overspeed 

region. 

Type Certification Basis 

Under the provisions of 14 CFR 21.17, 

Embraer S.A. must show that the Model 

EMB–550 airplane meets the applicable 

provisions of part 25, as amended by 

Amendments 25–1 through 25–127 

thereto. 

If the Administrator finds that the 

applicable airworthiness regulations 

(i.e., 14 CFR part 25) do not contain 

adequate or appropriate safety standards 

for the Model EMB–550 airplane 

because of a novel or unusual design 

feature, special conditions are 

prescribed under the provisions of 

§ 21.16. 

Special conditions are initially 

applicable to the model for which they 

are issued. Should the type certificate 

for that model be amended later to 

include any other model that 

incorporates the same or similar novel 

or unusual design feature, the special 

conditions would also apply to the other 

model under § 21.101. 

In addition to the applicable 

airworthiness regulations and special 

conditions, the Model EMB–550 

airplane must comply with the fuel vent 

and exhaust emission requirements of 

14 CFR part 34 and the noise 

certification requirements of 14 CFR 

part 36 and the FAA must issue a 

finding of regulatory adequacy under 

section 611 of Public Law 92–574, the 

‘‘Noise Control Act of 1972.’’ 

The FAA issues special conditions, as 

defined in 14 CFR 11.19, in accordance 

with § 11.38, and they become part of 

the type-certification basis under 

§ 21.17(a)(2). 

Novel or Unusual Design Features 

The Model EMB–550 airplane will 

incorporate the following novel or 

unusual design feature: an electronic 

flight control system which contains flyby-wire control laws, including 

envelope protections, for the overspeed 

protection and roll limiting function. 

Current part 25 requirements do not 

contain appropriate standards for high 

speed protection systems. 

Discussion 

As further discussed previously, a 

special condition is necessary in 

addition to the requirements of § 25.143 

for the operation of the high speed 

protection. The general intent is that the 

overspeed protection does not impede 

normal maneuvering and speed control 

and that the overspeed protection does 

not restrict or prevent emergency 

maneuvering. Therefore, these special 

conditions contain the additional safety 

standards that the Administrator 

considers necessary to establish a level 

of safety equivalent to that established 

by the existing airworthiness standards. 

Discussion of Comments 

Notice of proposed special conditions 

No. 25–12–12–SC for the Embraer S.A. 

Model EMB–550 airplanes was 

published in the Federal Register on 

November 20, 2012 (77 FR 69572). No 

comments were received, and the 

special conditions are adopted as 

proposed. 

Applicability 

As discussed above, these special 

conditions are applicable to the Model 

EMB–550 airplane. Should Embraer 

S.A. apply at a later date for a change 

to the type certificate to include another 

model incorporating the same novel or 

unusual design feature, the special 

conditions would apply to that model as 

well. 

Conclusion 

This action affects only certain novel 

or unusual design features on one model 

of airplanes. It is not a rule of general 

applicability. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

■ The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 

The Special Conditions 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the following special 

conditions are issued as part of the type 

certification basis for Embraer S.A. 

Model EMB–550 airplanes. 

1. In addition to § 25.143, the 

following requirement applies: 

Operation of the high speed limiter 

during all routine and descent 

procedure flight must not impede 

normal attainment of speeds up to 

overspeed warning. 

Issued in Renton, Washington, on February 

12, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–03676 Filed 2–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1005; Directorate 

Identifier 2012–NE–27–AD; Amendment 39– 

17349; AD 2013–03–14] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada Corp Turboshaft 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 


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11564 Federal Register / Vol. 78, No. 33 / Tuesday, February 19, 2013 / Rules and Regulations 

Pratt & Whitney Canada Corp. (P&WC) 

PT6C–67C turboshaft engines. This AD 

requires initial and repetitive borescope 

inspections to verify the presence of a 

retaining ring securing the power 

turbine (PT) baffle located near the 

second stage PT disk. If the engine fails 

the inspection, this AD also requires 

removing the engine from service before 

further flight. This AD was prompted by 

five reported incidents of second stage 

PT disk damage. We are issuing this AD 

to prevent damage to the PT disk which, 

if undetected, could cause uncontained 

PT disk failure and loss of control of the 

helicopter. 

DATES: This AD becomes effective 

March 26, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 26, 2013. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

email: james.lawrence@faa.gov; phone: 

781–238–7176; fax: 781–238–7199. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on October 25, 2012 (77 FR 

65142). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information states: 

There have been 5 reported incidents of 

second stage Power Turbine (PT) disk 

damage caused by the PT baffle moving and 

contacting the downstream side of the second 

stage PT disk. In two of these incidents, the 

PT section of the engine failed to rotate (on 

ground) as a result of baffle interference. 

An investigation has determined that the 

root cause for the PT baffle displacement and 

the resultant PT disk damage was due to the 

failure of the retaining ring that holds the PT 

baffle in its intended position. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 65142, October 25, 2012). 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed (77 FR 65142, October 25, 

2012). 

Costs of Compliance 

Based on the service information, we 

estimate that this AD will affect about 

220 engines of U.S. registry. We also 

estimate that it will take about six hours 

per engine to comply with this AD. The 

average labor rate is $85 per work-hour. 

We anticipate that two engines will fail 

the initial inspection. Required parts 

will cost about $224,636 per engine. 

Based on these figures, we estimate the 

cost of the AD on U.S. operators to be 

$561,472. Our cost estimate is exclusive 

of possible warranty coverage. 

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 this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

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 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 (phone: 

(800) 647–5527) is provided 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, Incorporation by reference, 

Safety. 

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 AD: 

2013–03–14 Pratt & Whitney Canada Corp: 

Amendment 39–17349; Docket No. 

FAA–2012–1005; Directorate Identifier 

2012–NE–27–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective March 26, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pratt & Whitney Canada 

Corp. (P&WC) PT6C–67C turboshaft engines 

that have not had P&WC Service Bulletin 

(SB) No. PT6C–72–41056 incorporated. 

(d) Reason 

This AD was prompted by five reported 

incidents of second stage power turbine (PT) 

disk damage. We are issuing this AD to 

prevent damage to the PT disk which, if 

undetected, could cause uncontained PT disk 

failure and loss of control of the helicopter. 

(e) Actions and Compliance 

Unless already done, do the following 

actions. 


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Federal Register / Vol. 78, No. 33 / Tuesday, February 19, 2013 / Rules and Regulations 11565 

(f) Borescope Inspections 

(1) Borescope-inspect to verify the 

presence of a retaining ring securing the PT 

baffle located near the second stage PT disk, 

as follows: 

(i) For engines with 2,200 PT cycles or 

more on the effective date of this AD, inspect 

within 100 operating hours or 150 PT cycles, 

whichever occurs first. 

(ii) For engines with more than 1,400 PT 

cycles but fewer than 2,200 PT cycles on the 

effective date of this AD, inspect within 250 

operating hours, 350 PT cycles, or before 

exceeding 2,350 PT cycles, whichever occurs 

first. 

(iii) For engines with 1,400 PT cycles or 

fewer on the effective date of this AD, inspect 

within 500 operating hours, 750 PT cycles, or 

before exceeding 1,750 PT cycles, whichever 

occurs first. 

(2) Thereafter, repetitively borescopeinspect to verify the presence of the retaining 

ring securing the PT baffle located near the 

second stage PT disk, on or before an 

additional 600 flight hours or 900 PT cycles, 

whichever occurs first. 

(3) Use P&WC Alert SB No. PT6C–72– 

A41060, Revision 3, dated October 11, 2012, 

paragraphs 3.A.(1) through 3.A.(6) to do the 

borescope inspections required by this AD. 

(4) If the retaining ring is missing or the PT 

baffle is out of position, then remove the 

engine from service before further flight. 

(g) Optional Terminating Action 

Performing the engine improvement 

modifications in P&WC SB No. PT6C–72– 

41056, Revision 5, dated January 17, 2013, 

paragraphs 3.A. through 3.C.(12) and 3.E.(1) 

through 3.E.(15), is an optional terminating 

action to the repetitive inspections required 

by this AD. 

(h) Credit for Previous Actions 

(1) If you performed the initial borescope 

inspection before the effective date of this AD 

using P&WC Special Instruction No. 45– 

2011R2, dated July 27, 2011, or P&WC Alert 

SB No. PT6C–72–A41060, dated August 12, 

2011, or Revision 1, dated September 29, 

2011, or Revision 2, dated February 10, 2012, 

you met the requirements of paragraph (f)(1) 

of this AD. 

(2) If you performed the engine 

modification before the effective date of this 

AD using P&WC SB No. PT6C–72–41056, 

dated April 1, 2011, or Revision 1, dated June 

17, 2011, or Revision 2, dated October 6, 

2011, or Revision 3, dated February 3, 2012, 

or Revision 4, dated February 13, 2012, you 

met the requirements of this AD and no 

further action is required. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(j) Related Information 

(1) For more information about this AD, 

contact James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

email: james.lawrence@faa.gov; phone: 781– 

238–7176; fax: 781–238–7199. 

(2) Refer to Transport Canada AD CF– 

2012–24, dated August 2, 2012, for related 

information. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Pratt & Whitney Canada Corp (P&WC) 

Alert Service Bulletin (SB) No. PT6C–72– 

A41060, Revision 3, dated October 11, 2012. 

(ii) P&WC SB No. PT6C–72–41056, 

Revision 5, dated January 17, 2013. 

(3) For service information identified in 

this AD, contact Pratt & Whitney Canada 

Corp., 1000 Marie-Victorin, Longueuil, 

Quebec, Canada, J4G 1A1; phone: 800–268– 

8000; fax: 450–647–2888; Web site: http:// 

www.pwc.ca. 

(4) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

(5) You may view this service information 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

February 1, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–03266 Filed 2–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0942; Directorate 

Identifier 2012–NE–24–AD; Amendment 39– 

17355; AD 2013–03–21] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada Corp. Turboshaft 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

serial number Pratt & Whitney Canada 

Corp. PW206B, PW206B2, PW206C, 

PW207C, PW207D, PW207D1, 

PW207D2, and PW207E turboshaft 

engines. This AD was prompted by the 

discovery that certain power turbine 

(PT) disks were made to specific heat 

codes that may not achieve the 

maximum in-service life. This AD 

requires re-identification of the PT disk 

to a part number (P/N) with a lower life 

limit. We are issuing this AD to prevent 

possible uncontained PT disk failure 

and loss of helicopter control. 

DATES: This AD becomes effective 

March 26, 2013. The Director of the 

Federal Register approved the 

incorporation by reference of a certain 

publication listed in this AD as of 

March 26, 2013. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7176; fax: 781–238– 

7199; email: james.lawrence@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on November 7, 2012 (77 FR 

66767). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information states: 

Certain power turbine (PT) disks, part 

number (P/N) 3044188–01, made to specific 

heat codes may not achieve the established 

maximum in-service life when installed in 

Turbomachinery Assembly P/N 3058588. The 

PT disk in-service life for engines using this 

specific PT disk and compressor turbine (CT) 

vane combination is reduced when operated 

in a particular temperature and speed 

environment. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 66767, November 7, 2012). 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed (77 FR 66767, November 7, 

2012). 

Costs of Compliance 

We estimate that this AD will affect 

about 83 engines installed on 


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