[Docket No. FAA-2015-2983; Directorate Identifier 2015-NE-20-AD; Amendment 

39-18383; AD 2016-02-04] 

RIN 2120-AA64 

Airworthiness Directives; CFM International S.A. Turbofan Engines 

AGENCY: Federal Aviation Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new airworthiness directive (AD) for certain CFM 

International S.A. (CFM) CFM56-5B series turbofan engines. This AD was prompted by 

a corrected lifing analysis by the engine manufacturer that shows the need to identify an 

initial and repetitive inspection threshold for certain part number (PIN) turbine rear 

frames (TRFs). This AD requires initial and repetitive inspections of certain PIN TRFs on 

the low-pressure turbine (LPT) frame assembly. We are issuing this AD to prevent failure 

of the TRF on the LPT frame assembly, which could lead to engine separation, damage to 

the engine, and damage to the airplane. 

DATES: This AD is effective [INSERT DATE 35 DAYS AFTER DATE OF 

PUBLICATION IN THE FEDERAL REGISTER]. 

The Director of the Federal Register approved the incorporation by reference of 

certain publications listed in this AD as of [INSERT DATE 35 DAYS AFTER DATE OF 

PUBLICATION IN THE FEDERAL REGISTER]. 

ADDRESSES: For service information identified in this AD, contact CFM International 

Inc., Aviation Operations Center, I Neumann Way, MID Room 285, Cincinnati, OH 

45125; phone: 877-432-3272; fax: 877-432-3329; email: aviation.fleetsupport@ge.com. 

You may view this service information at the FAA, Engine & Propeller Directorate, 1200 
You may examine the AD docket on the Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA-2015-2983; 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 address for the Docket Office (phone: 

800-647-5527) is Document Management Facility, U.S. Department of Transportation, 

Docket Operations, M-30, West Building Ground Floor, Room Wl2-140, 1200 New 

Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Kyle Gustafson, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District A venue, 

Burlington, MA 01803; phone: 781-238-7183; fax: 781-238-7199; email: 

kyle.gustafson@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by 

adding an AD that would apply to certain CFM CFM56-5B series turbofan engines. The 

NPRM published in the Federal Register on October 2, 2015 (80 FR 59672). The NPRM 

was prompted by a corrected lifing analysis by the engine manufacturer that shows the need to identify an initial and repetitive inspection threshold for certain PIN TRFs. The 

NPRM proposed to require initial and repetitive inspections of certain PIN TRFs on the 

LPT frame assembly. We are issuing this AD to correct the unsafe condition on these 

products. 

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Clarification to the Repetitive Inspection Requirements 

We have revised the Compliance, paragraph (e) of this AD, to clarify the 

repetitive inspection requirements for when the initial inspection is done prior to the 

initial inspection threshold. 

Conclusion 

We reviewed the relevant data and determined that air safety and the public 

interest require adopting this AD as proposed except for the changes described above. We 

have determined that the changes described above are minor changes, as they: 

• Are consistent with the intent that was proposed in the NPRM (80 FR 59672, 

October 2, 201 5) for correcting the unsafe condition; and 

• Do not add any additional burden upon the public than was already proposed 

in the NPRM (80 FR 59672, October 2, 2015). 

We also determined that these changes will not increase the economic burden on 

any operator or increase the scope of this AD. 

Related Service Information under 1 CFR part 51 

We reviewed CFM Service Bulletin (SB) No. CFM56-5B S/B 72-0850, dated 

December 19, 2012, which describes procedures for inspecting the TRF. This service 

information is reasonably available because the interested parties have access to it 

through their nonnal course of business or by the means identified in the ADDRESSES 

section of this final rule. 

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Costs of Compliance 

We estimate that this AD affects about 94 engines installed on airplanes of U.S. 

registry. We also estimate that it will take about 3 hours per engine to do the inspection. 

The average labor rate is $85 per hour. Based on these figures, we estimate the cost of 

this AD on U.S. operators to be $23,970. 

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. 

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(3) Will not affect intrastate aviation in Alaska to the extent that it justifies 

making a regulatory distinction, 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 14 CFR part 39 as follows: 

PART 39 - AIRWORTHINESS DIRECTIVES 

1. The authority citation for parthttp//www.continentalsanantonio.com 39 

continues to read as follows: 

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

§ 39.13 [Amended) 

2. The FAA amends§ 39.13 by adding the following new airworthiness directive 

(AD): 

2016-02-04 CFM International S.A.: Amendment 39-18383; Docket 

No. FAA-2015-2893; Directorate Identifier 2015-NE-20-AD. 

(a) Effective Date 

This AD is effective [INSERT DATE 35 DAYS AFTER DATE OF 

PUBLICATION IN THE FEDERAL REGISTER]. 

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turbine rear frame (TRF), part number (PIN) 338-102-907-0 or PIN 338-102-908-0, 

installed. 

(d) Unsafe Condition 

This AD was prompted by a corrected lifing analysis by the engine manufacturer 

that shows the need for an initial and repetitive inspection of certain PIN TRFs on the 

low-pressure turbine (LPT) frame assembly. We are issuing this AD to prevent failure of 

the TRF on the LPT frame assembly, which could lead to engine separation, damage to 

the engine, and damage to the airplane. 

(e) Compliance 

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

(1) For Engines that have Applied CFM Service Bulletin (SB) No. CFM56-SB SIB 

72-0308: 

(i) Prior to accumulating 25,000 cycles since new (CSN) on the TRF of the LPT 

frame assembly or within 150 cycles after the effective date of this AD, whichever occurs 

later, perform an initial eddy current inspection (ECI) or a f1uorescent penetrant 

inspection (FPI) of the TRF mount struts on the LPT assembly. 

(ii) For engines with unknown CSN on the TRF of the LPT frame assembly, 

perform the initial inspection required by this AD within 150 cycles-in-service (CIS) after 

the effective date of this AD. 

(iii) Use paragraph 3.8. in the Accomplishment Instructions ofCFM SB No. 

CFM56-5B SIB 72-0850, dated December 19, 2012, to do the ECl and paragraph 3.C. in 

the Accomplishment Instructions ofCFM SB No. CFM56-5B SIB 72-0850, to do the 

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25,000 CSN on the TRF of the LPT assembly, whichever occurs later. 

(v) If the cumulative length of all cracks found at any TRF mount strut location is 

less than 0.20 inches, repeat the inspection within 1,670 cycles CSLI. 

(vi) If the cumulative length of cracks found at any TRF mount strut location is 

greater than or equal to 0.20 inches, but less than 0.25 inches, repeat the inspection within 

280 CSLI. 

(vii) If the cumulative length of cracks found at any TRF mount strut location is 

0.25 inches or greater, replace the TRF with a part eligible for installation before further 

flight. (2) For Engines that have Not Applied CFM SB No. CFM56-5B SIB 72-0308: 

(i) Prior to accumulating 32,000 CSN on the TRF of the LPT frame assembly or 

within 150 cycles after the effective date of this AD, whichever occurs later, perform an 

initial ECI or FPI of the TRF mount struts on the LPT frame assembly. 

(ii) For engines with unknown CSN on the TRF of the LPT frame assembly, 

perform the initial inspection required by this AD within 150 CIS after the effective date 

of this AD. 

(iii) Use paragraph 3.8. in the Accomplishment Instructions of CFM SB No. 

CFM56-5B SIB 72-0850, dated December 19, 2012, to do the ECI and paragraph 3.C. in 

the Accomplishment Instructions of CFM SB No. CFM56-5B SIB 72-0850, to do the 

FPI. Do not include TRF mount strut crack lengths towards the cumulative crack length 

after the cracks are repaired. 

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less than 0.20 inches, repeat the inspection within 2,500 CSLI. 

(vi) If the cumulative length of cracks found at any TRF mount strut location is 

greater than or equal to 0.20 inches and less than 0.25 inches, repeat the inspection within 

370 CSLI. 

(vii) If the cumulative length of cracks found at any TRF mount strut location is 

0.25 inches or greater, replace the TRF with a part eligible for installation before further 

flight. 

(f) Alternative Methods of Compliance (AMOCs) 

The Manager, Engine Certification Office, FAA, may approve AMOCs for this 

AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email 

your request to: ANE-AD-AMOC@faa.gov. 

(g) Related Information 

(1) For more infom1ation about this AD, contact Kyle Gustafson, Aerospace 

Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 

District Avenue, Burlington, MA 01803; phone: 781-238-7183; fax: 781-238-7199; 

email: kyle.gustafson@faa.gov. 

(2) CFM SB No. CFM56-5B SIB 72-0308, which is not incorporated by reference 

in this AD, can be obtained from CFM, using the contact information in paragraph (h)(4) 

of this AD. 

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(2) You must use this service information as applicable to do the actions required 

by this AD, unless the AD specifies otherwise. 

(3) The following service information was approved for IBR on [INSERT DATE 

35 DAYS AFTER DATE OF PUBLICATION IN THE FEDERAL REGISTER]. 

(i) CFM International S. A. (CFM) Service Bulletin No. CFM56-5B SIB 72-0850, 

dated December 19,2012. 

(ii) Reserved. (4) For CFM service information identified in this AD, contact CFM International 

Inc., Aviation Operations Center, 1 Neumann Way, MID Room 285, Cincinnati, OH 

45125; phone: 877-432-3272; fax: 877-432-3329; email: aviation.fleetsupport@ge.com. 

(5) You may view this service information at the FAA, Engine & Propeller 

Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of 

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

(6) You may view tlus 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. 

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Gaetano Sciortino, 

Acting Directorate Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

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