Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Rules and Regulations 4169 

information. The street address for the 

Docket Operations office (telephone: 

800–647–5527) is in the ADDRESSES

section. 

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 airworthiness 

directive (AD): 

2016–02–03 Airbus: Amendment 39– 

18382. Docket No. FAA–2015–1429; 

Directorate Identifier 2014–NM–246–AD. 

(a) Effective Date 

This AD becomes effective March 1, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category, all manufacturer 

serial numbers. 

(1) Airbus Model A319–113 and –114 

airplanes. 

(2) Airbus Model A320–211 and –212 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 

(e) Reason 

This AD was prompted by a report that the 

aft mount pylon bolts of the CFM56–5 

engines may have been installed using the 

wrong torque values. We are issuing this AD 

to detect and correct improper torque of the 

aft mount pylon bolts, which, if combined 

with any maintenance damage, could lead to 

aft engine mount failure, possibly resulting in 

engine detachment and consequent reduced 

control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection for Incorrect Torque Values 

Within 6 months or 1,500 flight cycles, 

whichever occurs first after the effective date 

of this AD, inspect to determine the method 

used to install the engines, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–71–1063, 

including Appendix 01, dated August 13, 

2014. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the method used to install the 

engines can be conclusively determined from 

that review. For any engine replaced as 

specified in the Airbus A318/A319/A320/

A321 Aircraft Maintenance Manual (AMM), 

Task 71–00–00–400–040–A01, ‘‘Installation 

of the Power Plant with Engine Positioner 

TWW 75E,’’ dated May 2013: Within 6 

months or 1,500 flight cycles, whichever 

occurs first after the effective date of this AD, 

re-torque the 4 aft mount pylon bolts using 

a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA). 

Note 1 to paragraph (g) of this AD: 

Additional guidance for the re-torque can be 

found in Airbus A318/A319/A320/A321 

AMM Task 71–00–00–400–040–A01, 

‘‘Installation of the Power Plant with Engine 

Positioner TWW 75E,’’ dated May 2014. 

(h) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install a CFM56–5 engine, on any 

airplane, unless the inspection, and, as 

applicable, the re-torque, is done as specified 

in paragraph (g) of this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–1405; fax: 425–227– 

1149. Information may be emailed to: 9-116- 

AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2014–0258, dated November 28, 2014, for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov/#!document

Detail;D=FAA-2015-1429-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (k)(3) and (k)(4) of this AD. 

(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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A320–71–1063, 

including Appendix 01, dated August 13, 

2014. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone: +33 5 61 93 36 96; fax: +33 5 61 

93 44 51; email: account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this 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/cfr/ibr-locations.html. 

Issued in Renton, Washington, on January 

11, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–01108 Filed 1–25–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1991; Directorate 

Identifier 2014–NM–251–AD; Amendment 

39–18381; AD 2016–02–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A318–111 and –112 

airplanes; Model A319–111, –112, and 

–115 airplanes; Model A320–214 

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4170 Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Rules and Regulations 

airplanes; and Model A321–111, –112, 

–211, –212, and –213 airplanes. This AD 

was prompted by reports of cracked 

cadmium-plated lock nuts that attach 

the hinge to the fan cowl door. This AD 

requires inspecting to determine the 

serial number of each engine fan cowl 

door, inspecting for cracking of the 

hinge lock nuts of any affected door, 

and replacing the lock nuts if necessary. 

We are issuing this AD to detect and 

correct cracking of the hinge lock nuts, 

which could result in separation of the 

hinge from the fan cowl door, in-flight 

loss of the door, and consequent damage 

to the airplane. 

DATES: This AD becomes effective 

March 1, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 1, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://www.

regulations.gov/#!docketDetail;D=FAA2015-1991; 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. 

For service information identified in 

this final rule, contact the following: 

For Airbus service information 

contact Airbus, Airworthiness Office— 

EIAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; 

telephone: +33 5 61 93 36 96; fax: +33 

5 61 93 44 51; email: account.airwortheas@airbus.com; Internet http://

www.airbus.com. 

For Goodrich service information 

contact Goodrich Aerostructures, 850 

Lagoon Drive, Chula Vista, California, 

91910–2098; telephone: 619–691–2719; 

email: jan.lewis@goodrich.com; Internet: 

http://www.goodrich.com/TechPubs. 

You may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1991. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

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 all Airbus Model A318–111 

and –112 airplanes; Model A319–111, 

–112, and –115 airplanes; Model A320– 

214 airplanes; and Model A321–111, 

–112, –211, –212, and –213 airplanes. 

The NPRM published in the Federal 

Register on July 2, 2015 (80 FR 38036). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0276, dated December 

19, 2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for all Airbus 

Model A318–111 and –112 airplanes; 

Model A319–111, –112, and –115 

airplanes; Model A320–214 airplanes; 

and Model A321–111, 112, –211, –212, 

and –213 airplanes. The MCAI states: 

In-service findings have been reported of 

cracked cadmium plated lock nuts. This 

cracking occurs shortly after installation. 

Investigation results attribute the cause to an 

improper manufacturing procedure of the 

nuts. It was determined that the affected 

batch of lock nuts was used on the fan cowl 

to attach hinges to the cowl doors on 

CFM56–5B engines only. 

This condition, if not corrected, could lead 

to separation of the hinge from the fan cowl 

door, possibly resulting in in-flight loss of a 

fan cowl door, with consequent damage to 

the aeroplane and/or injury to persons on the 

ground. 

For the reasons describes above, this 

[EASA] AD required identification of the 

affected fan cowl doors, a one-time 

inspection of the fan cowl door hinge nuts 

and, depending on findings, replacement of 

the affected nuts. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/#!documentDetail;

D=FAA-2015-1991-0003. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 38036, July 2, 2015) 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 this AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 

38036, July 2, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 38036, 

July 2, 2015). 

Related Service Information under 1 

CFR part 51 

Airbus has issued Service Bulletin 

A320–71–1062, dated July 28, 2014. 

Goodrich Aerostructures has issued 

Service Bulletin RA32071–151, dated 

June 11, 2014. The service information 

describes procedures for inspection and 

replacement of the hinge nuts of the fan 

cowl door. This service information is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 437 

airplanes of U.S. registry. 

We also estimate that it takes about 2 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $0 per 

product. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $74,290, or $170 per 

product. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this AD. 

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 

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Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Rules and Regulations 4171 

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 the 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://www.regulations.

gov/#!docketDetail;D=FAA–2015–1991; 

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 Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

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 airworthiness 

directive (AD): 

2016–02–02 Airbus: Amendment 39–18381. 

Docket No. FAA–2015–1991; Directorate 

Identifier 2014–NM–251–AD. 

(a) Effective Date 

This AD becomes effective March 1, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes, 

certificated in any category, identified in 

paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of 

this AD, all manufacturer serial numbers. 

(1) Airbus Model A318–111 and –112 

airplanes. 

(2) Airbus Model A319–111, –112, and 

–115 airplanes. 

(3) Airbus Model A320–214 airplanes. 

(4) Airbus Model A321–111, –112, –211, 

–212, and –213 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 

(e) Reason 

This AD was prompted by reports of 

cracked cadmium-plated lock nuts that attach 

the hinge to the fan cowl door. We are 

issuing this AD to detect and correct cracking 

of the hinge lock nuts, which could result in 

separation of the hinge from the fan cowl 

door, the in-flight loss of the door, and 

consequent damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspect to Determine Serial Number 

Within 24 months after the effective date 

of this AD: Inspect to determine if any fan 

cowl door has a serial number 10029001 

through 11092003 inclusive, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–71–1062, 

dated July 28, 2014; or Goodrich 

Aerostructures Service Bulletin RA32071– 

151, dated June 11, 2014. A review of 

airplane maintenance records is acceptable in 

lieu of the inspection required by this 

paragraph, provided those records can be 

relied upon for that purpose and the serial 

number can be positively identified by that 

review. 

(h) Inspection and Replacement 

For any fan cowl door having any serial 

number identified in paragraph (g) of this 

AD: Within 24 months after the effective date 

of this AD, do a detailed inspection for 

cracking of the hinge lock nuts of the door, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

71–1062, dated July 28, 2014; or Goodrich 

Aerostructures Service Bulletin RA32071– 

151, dated June 11, 2014. If any crack is 

found, before further flight, replace each 

cracked hinge lock nut, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–71–1062, dated July 

28, 2014; or Goodrich Aerostructures Service 

Bulletin RA32071–151, dated June 11, 2014. 

(i) Special Flight Permits 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–1405; fax: 425–227– 

1149. Information may be emailed to: 9– 

ANM–116–AMOC–REQUESTS@faa.gov. 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0276, dated 

December 19, 2014, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.

gov/#!documentDetail;D=FAA-2015-1991- 

0003. 

(l) 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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A320–71–1062, 

dated July 28, 2014. 

(ii) Goodrich Aerostructures Service 

Bulletin RA32071–151, dated June 11, 2014. 

(3) For Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone: +33 5 61 93 36 96; fax: 

+33 5 61 93 44 51; email: account.airwortheas@airbus.com; Internet http://

www.airbus.com. 

(4) For Goodrich service information 

identified in this AD, contact Goodrich 

Aerostructures, 850 Lagoon Drive, Chula 

Vista, California, 91910–2098; telephone: 

619–691–2719; email: jan.lewis@

goodrich.com; Internet: http://www.goodrich.

com/TechPubs. 

(5) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(6) You may view this service information 

that is incorporated by reference at the 

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4172 Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Rules and Regulations 

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/ibr-locations.html. 

Issued in Renton, Washington, on January 

9, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00952 Filed 1–25–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[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 (P/N) turbine rear 

frames (TRFs). This AD requires initial 

and repetitive inspections of certain P/ 

N 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 March 1, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 1, 2016. 

ADDRESSES: For service information 

identified in this AD, contact CFM 

International Inc., Aviation Operations 

Center, 1 Neumann Way, M/D 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 District Avenue, Burlington, MA. 

For information on the availability of 

this material at the FAA, call 781–238– 

7125. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2015–2983. 

Examining the AD Docket 

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 W12–140, 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 

Avenue, 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 P/N TRFs. The NPRM proposed 

to require initial and repetitive 

inspections of certain P/N TRFs on the 

LPT frame assembly. We are issuing this 

AD to correct the unsafe condition on 

these products. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 59672, October 2, 2015) or on the 

determination of the cost to the public. 

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, 2015) 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 normal 

course of business or by the means 

identified in the ADDRESSES section of 

this final rule. 

Other Related Service Information 

We also reviewed CFM SB No. 

CFM56–5B S/B 72–0308. Operators 

subject to this AD are required to follow 

different initial and repetitive 

inspection intervals depending on 

whether CFM SB No. CFM56–5B S/B 

72–0308 has been applied. 

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 

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