This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents.

Rules and Regulations Federal Register

45173 

Vol. 82, No. 187 

Thursday, September 28, 2017 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9451; Product 

Identifier 2016–NE–24–AD; Amendment 39– 

19058; AD 2017–20–01] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Honeywell International Inc. 

(Honeywell) TFE731–20 and TFE731–40 

turbofan engines. This AD was 

prompted by two fan disks found with 

a manufacturing-caused flaw. This AD 

requires removing affected fan disks and 

replacing fan disks with a part eligible 

for installation. We are issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective November 2, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 2, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Honeywell International Inc., 111 S. 

34th Street, Phoenix, AZ 85034–2802; 

phone: 800–601–3099; Internet: https:// 

myaerospace.honeywell.com/wps/ 

portal. You may view this service 

information at the FAA, Engine and 

Propeller Standards Branch, 1200 

District Avenue, Burlington, MA 01803. 

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–2016–9451. 

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–2016– 

9451; 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 final rule, 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: 

Joseph Costa, Aerospace Engineer, Los 

Angeles ACO Branch, FAA, 3960 

Paramount Blvd., Lakewood, CA 90712– 

4137; phone: 562–627–5246; fax: 562– 

627–5210; email: joseph.costa@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 all Honeywell TFE731–20 and 

TFE731–40 turbofan engines. The 

NPRM published in the Federal 

Register on March 7, 2017 (82 FR 

12755). The NPRM was prompted by 

two fan disks found with a 

manufacturing-caused flaw. The NPRM 

proposed to require removing the 

affected fan disks, performing a onetime inspection, and replacing fan disks 

that fail inspection. We are issuing this 

AD to prevent uncontained failure of the 

fan disks, damage to the engine, and 

damage to the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

We have considered the comment 

received. 

Miscellaneous Comment 

We received a comment regarding 

Honeywell as a company that was not 

relevant to this AD. No further 

discussion is required. 

Changes to This AD 

Based on further review, we made the 

following changes to this AD. 

We corrected the cost per product 

estimate under ‘‘On-condition costs’’ in 

the Costs of Compliance section of the 

NPRM from $300,510 to $50,085 in this 

AD. The cost per product in the NPRM 

incorrectly estimated the cost for six 

engines rather than for one engine. On 

further review, we also redefined the 

work hours needed to install the new or 

reworked fan disk. The 8 work hours to 

inspect the fan disk were listed as a 

separate item in the NPRM but, in this 

final rule, we added these work hours 

to the estimated cost of installing the 

reworked or new fan disk. The overall 

estimated cost of this work per engine 

remains the same. 

We corrected the product 

identification from ‘‘Honeywell 

International Inc. (Type Certificate 

previously held by AlliedSignal Inc., 

Garrett Engine Division; Garrett Turbine 

Engine Company; and AiResearch 

Manufacturing Company of Arizona)’’ to 

‘‘Honeywell International Inc. (Type 

Certificate previously held by 

AlliedSignal Inc.).’’ 

We removed paragraph (g)(4) of the 

NPRM which required inspection of the 

removed fan disks in accordance with 

paragraph 3.D.(2) in the 

Accomplishment Instructions of 

Honeywell SB TFE731–72–5256, 

Revision 0, dated October 7, 2016. 

Although fan disks may be returned to 

Honeywell for inspection and rework to 

become eligible for installation, that is 

not a requirement of this AD. 

We revised the definition of ‘‘parts 

eligible for installation’’ in paragraph (g) 

of this AD to read: ‘‘For the purposes of 

this AD, parts eligible for installation 

are: (i) Fan disks not listed in the 

Accomplishment Instructions, Table 9, 

in Honeywell SB TFE731–72–5256, 

Revision 0, dated October 7, 2016; or (ii) 

fan disks listed in Table 9 that have 

been inspected, reworked, and marked 

with ‘‘T43374’’ adjacent to the P/N or S/ 

N. Guidance on returning affected parts 

to Honeywell for inspection and rework 

is found in the Accomplishment 

Instructions, paragraph 3.D., of 

Honeywell SB TFE731–72–5256.’’ This 

definition clarifies that fan disks with a 

P/N not affected by this AD, as well as 

parts that have been reworked and 

remarked, are eligible for installation. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 


jstallworth on DSKBBY8HB2PROD with RULES
45174 Federal Register / Vol. 82, No. 187 / Thursday, September 28, 2017 / Rules and Regulations 

public interest require adopting this 

final rule as proposed for minor 

editorial changes and the additional 

changes explained above. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Honeywell Service 

Bulletin (SB) TFE731–72–5256, 

Revision 0, dated October 7, 2016. The 

SB identifies affected fan disks by serial 

number and describes procedures for 

removing, inspecting, and replacing the 

fan disks. This service information is 

available by the means identified in the 

ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 61 

engines installed on 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 

Remove fan disk ............................................. 8 work-hours × $85 per hour = $680 ............. $0 $680 $41,480 

Install reworked or new fan disk ..................... 26 work-hours × $85 per hour = $2,210 ........ 0 2,210 134,810 

We estimate the following costs to do 

any necessary disk replacements that 

would be required based on the results 

of the required inspection. We estimate 

that 6 engines will need this 

replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace non-serviceable disks with new fan disk ....... 1 work-hour × $85 per hour = $85 ............................... $50,000 $50,085 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to engines, propellers, and 

appliances to the Manager, Engine and 

Propeller Standards Branch, Policy and 

Innovation Division. 

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 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 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): 

2017–20–01 Honeywell International Inc. 

(Type Certificate previously held by 

AlliedSignal Inc.): Amendment 39– 

19058; Docket No. FAA–2016–9451; 

Product Identifier 2016–NE–24–AD. 

(a) Effective Date 

This AD is effective November 2, 2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Honeywell 

International Inc. (Honeywell) TFE731–20 

and TFE731–40 turbofan engines, with a fan 

disk, part number (P/N) 3060287–2, and a 


jstallworth on DSKBBY8HB2PROD with RULES
Federal Register / Vol. 82, No. 187 / Thursday, September 28, 2017 / Rules and Regulations 45175 

serial number (S/N) listed in Table 9 of 

Honeywell Service Bulletin (SB) TFE731–72– 

5256, Revision 0, dated October 7, 2016, that 

do not have ‘‘T43374’’ marked adjacent to the 

engine P/N or S/N. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7230, Turbine Engine Compressor 

Section. 

(e) Unsafe Condition 

This AD was prompted by a report of two 

fan disks found with surface rollovers in the 

dovetail slot area. We are issuing this AD to 

prevent uncontained failure of the fan disks, 

damage to the engine, and damage to the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Remove the fan disk using the following 

criteria: 

(1) Remove fan disks with 9,000 cyclessince-new (CSN) or more on the effective 

date of this AD, within 100 cycles-in-service 

(CIS), or at the next engine shop visit, or at 

next access, whichever occurs first, after the 

effective date of this AD. 

(2) Remove fan disks with between 8,000 

and 8,999 CSN, inclusive, on the effective 

date of this AD, within 9,100 CSN or within 

1,000 CIS, or at the next engine shop visit, 

or at next access, whichever occurs first, after 

the effective date of this AD. 

(3) Remove fan disks with fewer than 8,000 

CSN, on the effective date of this AD, before 

exceeding 9,000 CSN, or at the next engine 

shop visit, or at next access, whichever 

occurs first, after the effective date of this 

AD. 

(4) Replace all removed fan disks with a 

part eligible for installation. 

(h) Definitions 

(1) For the purposes of this AD, an engine 

shop visit is defined as the removal of the tieshaft nut from the engine. 

(2) For the purposes of this AD, access is 

defined as the removal of the fan rotor 

assembly from the engine. 

(3) For the purposes of this AD, parts 

eligible for installation are: 

(i) fan disks not listed in the 

Accomplishment Instructions, Table 9, in 

Honeywell SB TFE731–72–5256, Revision 0, 

dated October 7, 2016; or 

(ii) fan disks listed in Table 9, in 

Honeywell SB TFE731–72–5256, Revision 0, 

dated October 7, 2016, that have been 

inspected, reworked, and marked with 

‘‘T43374’’ adjacent to the P/N or S/N. 

Guidance on returning affected parts to 

Honeywell for inspection and rework is 

found in the Accomplishment Instructions, 

paragraph 3.D., of Honeywell SB TFE731– 

72–5256. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles ACO Branch, 

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 manager of the 

Los Angeles ACO Branch, send it to the 

attention of the person identified in 

paragraph (j) 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. 

(j) Related Information 

For more information about this AD, 

contact Joseph Costa, Aerospace Engineer, 

Los Angeles ACO Branch, FAA, 3960 

Paramount Blvd., Lakewood, CA 90712– 

4137; phone: 562–627–5246; fax: 562–627– 

5210; email: joseph.costa@faa.gov. 

(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) Honeywell Service Bulletin TFE731–72– 

5256, Revision 0, dated October 7, 2016. 

(ii) Reserved. 

(3) For Honeywell service information 

identified in this AD, contact Honeywell 

International Inc., 111 S. 34th Street, 

Phoenix, AZ 85034–2802; phone: 800–601– 

3099; Internet: https://myaerospace.

honeywell.com/wps/portal. 

(4) You may view this service information 

at FAA, Engine and Propeller Standards 

Branch, 1200 District Avenue, 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/ibr-locations.html. 

Issued in Burlington, Massachusetts, on 

September 21, 2017. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2017–20776 Filed 9–27–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0753; Product 

Identifier 2017–NE–25–AD; Amendment 39– 

19046; AD 2017–2017–19–16] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Rolls-Royce plc (RR) RB211 Trent 553– 

61, Trent 553A2–61, Trent 556–61, 

Trent 556A2–61, Trent 556B–61, Trent 

556B2–61, Trent 560–61, and Trent 

560A2–61 turbofan engines. This AD 

requires replacement of the lowpressure compressor (LPC) case A-frame 

hollow locating pins. This AD was 

prompted by LPC case A-frame hollow 

locating pins that may have reduced 

integrity due to incorrect heat treatment. 

We are issuing this AD to correct the 

unsafe condition on these products. 

DATES: This AD becomes effective 

October 13, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publications listed in this 

AD as of October 13, 2017. 

We must receive comments on this 

AD by November 13, 2017. 

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. 

• Mail: U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

For service information identified in 

this AD, contact Rolls-Royce plc, 

Corporate Communications, P.O. Box 

31, Derby, England, DE24 8BJ; phone: 

011–44–1332–242424; fax: 011–44– 

1332–249936; email: http://www.rollsroyce.com/contact/civil_team.jsp; 

Internet: https://customers.rollsroyce.com/public/rollsroycecare. You 

may view this service information at the 

FAA, Engine and Propeller Standards 

Branch, Policy and Innovation Division, 


jstallworth on DSKBBY8HB2PROD with RULES