43634 Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2008–0118, dated June 27, 2008; 

and EADS CASA Service Bulletin SB–235– 

30–16, dated January 21, 2005; for related 

information. 

Material Incorporated by Reference 

(i) You must use EADS CASA Service 

Bulletin SB–235–30–16, dated January 21, 

2005, to do the actions required by this AD, 

unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact EADS–CASA, Military 

Transport Aircraft Division (MTAD), 

Integrated Customer Services (ICS), 

Technical Services, Avenida de Arago ́n 404, 

28022 Madrid, Spain; telephone +34 91 585 

55 84; fax +34 91 585 55 05; e-mail 

MTA.TechnicalService@casa.eads.net; 

Internet http://www.eads.net. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

service information that is incorporated by 

reference 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on August 

17, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–20581 Filed 8–26–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0174; Directorate 

Identifier 2008–NE–03–AD; Amendment 39– 

15997; AD 2009–18–01] 

RIN 2120–AA64 

Airworthiness Directives; CFM 

International, S.A. CFM56–5B1/P; –5B2/ 

P; –5B3/P; –5B3/P1; –5B4/P; –5B4/P1; 

–5B5/P; –5B6/P; –5B7/P; –5B8/P; –5B9/ 

P; –5B1/3; –5B2/3; –5B3/3; –5B4/3; 

–5B5/3; –5B6/3; –5B7/3; –5B8/3; –5B9/ 

3; –5B3/3B1; and –5B4/3B1 Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for CFM 

International, S.A. CFM56–5B1/P; –5B2/ 

P; –5B3/P; –5B3/P1; –5B4/P; –5B4/P1; 

–5B5/P; –5B6/P; –5B7/P; –5B8/P; –5B9/ 

P; –5B1/3; –5B2/3; –5B3/3; –5B4/3; 

–5B5/3; –5B6/3; –5B7/3; –5B8/3; –5B9/ 

3; –5B3/3B1; and –5B4/3B1 turbofan 

engines. This AD requires initial and 

repetitive eddy current inspections 

(ECIs) of certain part number (P/N) lowpressure (LP) turbine rear frames. This 

AD results from a refined lifing analysis 

by the engine manufacturer that shows 

the need to identify initial and 

repetitive inspection thresholds for 

inspecting certain LP turbine rear 

frames. We are issuing this AD to detect 

low-cycle-fatigue cracks in the LP 

turbine rear frame, which could result 

in an engine separating from the 

airplane, causing damage to, and 

possibly leading to loss of control of the 

airplane. 

DATES: This AD becomes effective 

October 1, 2009. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of October 1, 2009. 

ADDRESSES: You can get the service 

information identified in this AD from 

CFM International, Technical 

Publications Department, 1 Neumann 

Way, Cincinnati, OH 45215; telephone 

(513) 552–2800; fax (513) 552–2816. 

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: 

Stephen Sheely, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: 

stephen.k.sheely@faa.gov; telephone 

(781) 238–7750; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD and a supplemental 

proposed AD. The proposed AD applies 

to CFM International, S.A. CFM56–5B1/ 

P; –5B2/P; –5B3/P; –5B3/P1; –5B4/P; 

–5B4/P1; –5B5/P; –5B6/P; –5B7/P; 

–5B8/P; and –5B9/P turbofan engines, 

and the supplemental proposed AD 

applies to CFM International, S.A. 

CFM56–5B1/P; –5B2/P; –5B3/P; –5B3/ 

P1; –5B4/P; –5B4/P1; –5B5/P; –5B6/P; 

–5B7/P; –5B8/P; –5B9/P; –5B1/3; –5B2/ 

3; –5B3/3; –5B4/3; –5B5/3; –5B6/3; 

–5B7/3; –5B8/3; –5B9/3; –5B3/3B1; and 

–5B4/3B1 turbofan engines. We 

published the proposed AD in the 

Federal Register on May 7, 2008 (73 FR 

25597). That action proposed to require 

initial and repetitive ECIs of certain 

P/N LP turbine rear frames. We 

published the supplemental proposed 

AD in the Federal Register on April 24, 

2009 (74 FR 18662). That action 

proposed to require initial and 

repetitive ECIs of those same P/N LP 

turbine rear frames, to add two 

additional P/N LP turbine rear frames, 

to add 11 engine models to the 

applicability, and to clarify the 

commercial and corporate engines/LP 

turbine rear frames applicability. 

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 provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment received. 

One commenter, CFM International, 

S.A. requests that we reference the latest 

European Aviation Safety Agency AD 

2009–0110, dated May 7, 2009, as it is 

up-to-date on P/Ns and engine models 

affected. 

We agree and changed the AD to 

reference AD 2009–0110. 


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Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations 43635 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

282 CFM56–5B series turbofan engines 

installed on airplanes of U.S. registry. 

We estimate that it will take about 3 

work-hours to perform an eddy current 

inspection of an LP turbine rear frame. 

The average labor rate is $80 per workhour. A replacement LP turbine rear 

frame costs about $102,240. If all 282 LP 

turbine rear frames needed replacement, 

we estimate the total cost of the AD to 

U.S. operators to be $28,899,360. 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 have 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 summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

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 Federal Aviation Administration 

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: 

2009–18–01 CFM International, S.A.: 

Amendment 39–15997. Docket No. 

FAA–2008–0174; Directorate Identifier 

2008–NE–03–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 1, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to: 

(1) CFM International, S.A. turbofan 

engines with a low-pressure (LP) turbine rear 

frame, part number (P/N) 338–171–703–0; 

338–171–704–0; 338–171–705–0; or 338– 

171–706–0 installed, as follows: 

(i) Commercial application CFM56–5B1/P; 

–5B2/P; –5B3/P; –5B3/P1; –5B4/P; –5B4/P1; 

–5B5/P; –5B6/P; –5B7/P; –5B8/P; –5B9/P 

turbofan engines. 

(ii) Corporate application CFM56–5B6/P 

and –5B7/P turbofan engines. 

(2) CFM International, S.A. turbofan 

engines with an LP turbine rear frame, P/N 

338–171–751–0; or 338–171–752–0 installed, 

on corporate and commercial applications of 

CFM56–5B1/P; –5B2/P; –5B3/P; –5B3/P1; 

–5B4/P; –5B4/P1; –5B5/P; –5B6/P; –5B7/P; 

–5B8/P; –5B9/P; –5B1/3; –5B2/3; –5B3/3; 

–5B4/3; –5B5/3; –5B6/3; –5B7/3; –5B8/3; 

–5B9/3; –5B3/3B1; and –5B4/3B1 turbofan 

engines. 

(3) These engines are installed on, but not 

limited to, Airbus A318, A319, A320, and 

A321 series airplanes. 

Unsafe Condition 

(d) This AD results from a refined lifing 

analysis by the engine manufacturer that 

shows the need to identify initial and 

repetitive inspection thresholds for 

inspecting certain LP turbine rear frames. We 

are issuing this AD to detect low-cyclefatigue cracks in the LP turbine rear frame, 

which could result in an engine separating 

from the airplane, causing damage to, and 

possibly leading to loss of control of the 

airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Initial Inspection 

(f) Perform an initial eddy current 

inspection (ECI) of the LP turbine rear frame 

using paragraphs 3.A. through 3.A.(7)(d) of 

the Accomplishment Instructions of CFM 

International, S.A. Service Bulletin (SB) No. 

CFM56–5B S/B 72–0620, Revision 2, dated 

December 1, 2008, at the following 

compliance times: 

(1) For commercial engine applications, 

within 25,000 cycles-since-new (CSN) on the 

LP turbine rear frame. 

(2) For corporate engine applications, 

within 19,000 CSN on the LP turbine rear 

frame. 

(3) For engines with unknown LP turbine 

rear frame CSN, within 300 cycles-in-service 

from the effective date of this AD. 

Repetitive Inspections 

(g) Perform repetitive ECIs of the LP 

turbine rear frame using paragraphs 3.A. 

through 3.A.(7)(d) of the Accomplishment 

Instructions of CFM International, S.A. SB 

No. CFM56–5B S/B 72–0620, Revision 2, 

dated December 1, 2008. Use the inspection 

intervals in paragraph 3.A.(8) of the 

Accomplishment Instructions of CFM 

International, S.A. SB No. CFM56–5B S/B 

72–0620, Revision 2, dated December 1, 

2008. 

LP Turbine Rear Frame Removal Criteria 

(h) Remove LP turbine rear frames from 

service that have a single crack length of 2.56 

inches (65 mm) or longer, or multiple cracks 

with an accumulated crack length of 2.56 

inches (65 mm) or longer. 

Previous Credit 

(i) Initial and repetitive inspections done 

before the effective date of this AD using 

CFM International, S.A. SB No. CFM56–5B 

S/B 72–0620, dated May 3, 2007, or SB No. 

CFM56–5B S/B 72–0620, Revision 1, dated 

December 20, 2007, comply with the initial 

and repetitive inspection requirements 

specified in this AD. Operators must 

continue performing the repetitive 

inspections required in paragraph (g) of this 

AD. 

Alternative Methods of Compliance 

(j) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 


srobinson on DSKHWCL6B1PROD with RULES
43636 Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations 

Related Information 

(k) European Aviation Safety Agency AD 

2009–0110, dated May 7, 2009, also 

addresses the subject of this AD. 

(l) Contact Stephen Sheely, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: stephen.k.sheely@faa.gov; 

telephone (781) 238–7750; fax (781) 238– 

7199, for more information about this AD. 

Material Incorporated by Reference 

(m) You must use CFM International, S.A. 

SB No. CFM56–5B S/B 72–0620, Revision 2, 

dated December 1, 2008 to perform the 

inspections required by this AD. The Director 

of the Federal Register approved the 

incorporation by reference of this service 

bulletin in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. Contact CFM 

International, Technical Publications 

Department, 1 Neumann Way, Cincinnati, 

OH 45215; telephone (513) 552–2800; fax 

(513) 552–2816, for a copy of this service 

information. You may review copies at the 

FAA, New England Region, 12 New England 

Executive Park, Burlington, MA; or 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 

August 17, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–20284 Filed 8–26–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0622; Directorate 

Identifier 2009–CE–034–AD; Amendment 

39–15999; AD 2009–18–03] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Models PC–6, PC–6–H1, 

PC–6–H2, PC–6/350, PC–6/350–H1, PC– 

6/350–H2, PC–6/A, PC–6/A–H1, PC–6/ 

A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/ 

B2–H2, PC–6/B2–H4, PC–6/C–H2, and 

PC–6/C1–H2 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued 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: 

Findings of corrosion, wear and cracks in 

the upper wing strut fittings on some PC–6 

aircraft have been reported in the past. It is 

possible that the spherical bearing of the 

wing strut fittings installed in the underwing 

can be loose in the fitting or cannot rotate 

because of corrosion. In this condition, the 

joint cannot function as designed and fatigue 

cracks may then develop. Undetected cracks, 

wear and/or corrosion in this area could 

cause failure of the upper attachment fitting, 

leading to failure of the wing structure and 

subsequent loss of control of the aircraft. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

October 1, 2009. 

On October 1, 2009, the Director of 

the Federal Register approved the 

incorporation by reference of Pilatus 

Aircraft Ltd. Pilatus PC–6 Service 

Bulletin No. 57–005, REV No. 2, dated 

May 19, 2008, and Chapter 57–00–02 of 

Pilatus Aircraft Ltd. Pilatus PC–6 

Aircraft Maintenance Manual, dated 

November 30, 2008 (referenced as 

revision 9 in European Aviation Safety 

Agency (EASA) AD No.: 2007–0241R3), 

listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090. 

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 July 8, 2009 (74 FR 32471), 

and proposed to supersede AD 2007– 

19–14, Amendment 39–15205 (72 FR 

53920, September 21, 2007). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Findings of corrosion, wear and cracks in 

the upper wing strut fittings on some PC–6 

aircraft have been reported in the past. It is 

possible that the spherical bearing of the 

wing strut fittings installed in the underwing 

can be loose in the fitting or cannot rotate 

because of corrosion. In this condition, the 

joint cannot function as designed and fatigue 

cracks may then develop. Undetected cracks, 

wear and/or corrosion in this area could 

cause failure of the upper attachment fitting, 

leading to failure of the wing structure and 

subsequent loss of control of the aircraft. 

To address this problem, FOCA published 

AD TM–L Nr. 80.627–6/Index 72–2 and HB– 

2006–400 and EASA published AD 2007– 

0114 to require specific inspections and to 

obtain a fleet status. Since the issuance of AD 

2007–0114, the reported data proved that it 

was necessary to establish and require 

repetitive inspections. 

EASA published Emergency AD 2007– 

0241–E to extend the applicability and to 

require repetitive eddy current and visual 

inspections of the upper wing strut fitting for 

evidence of cracks, wear and/or corrosion 

and examination of the spherical bearing and 

replacement of cracked fittings. Collected 

data received in response to Emergency AD 

2007–0241–E resulted in the issuance of 

EASA AD 2007–0241R1 that permitted 

extending the intervals for the repetitive 

eddy current and visual inspections from 100 

Flight Hours (FH) to 300 FH and from 150 

Flight Cycles (FC) to 450 FC, respectively. In 

addition, oversize bolts were introduced by 

Pilatus PC–6 Service Bulletin (SB) 57–005 R1 

and the fitting replacement procedure was 

adjusted accordingly. 

Based on fatigue test results, EASA AD 

2007–0241R2 was issued to extend the 

repetitive inspection interval to 1 100 FH or 

12 calendar months, whichever occurs first, 

and to delete the related flight cycle intervals 

and the requirement for the ‘‘Mild Corrosion 

Severity Zone’’. In addition, some editorial 

changes have been made for reasons of 

standardization and readability. 

Revision 3 of this AD refers to the latest 

revision of the PC–6 Aircraft Maintenance 

Manual (AMM) Chapter 5 limitations which 

includes the same repetitive inspection 

intervals and procedures already mandated 

in the revision 2 of AD 2007–0241. Besides 

the inspections, the latest revision of the PC– 

6 AMM contains the replacement procedures 

for the fittings. 

Additionally, it is possible to replace the 

wing strut fitting with a new designed wing 

strut fitting. With this optional part 

replacement, in the repetitive inspection 

procedure the 1 100 FH interval is deleted so 

that only calendar defined intervals of 

inspections remain applicable. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 


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