Federal Register / Vol. 83, No. 172 / Wednesday, September 5, 2018 / Rules and Regulations 45041 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0416; Product 

Identifier 2017–NM–164–AD; Amendment 

39–19388; AD 2018–18–09] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Defense and Space S.A. (Formerly 

Known as Construcciones 

Aeronauticas, S.A.) 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 Defense and Space S.A. Model 

CN–235, CN–235–100, CN–235–200, 

and CN–235–300 airplanes; and certain 

Model C–295 airplanes. This AD was 

prompted by a report that cracks were 

found on the stabilizer-to-fuselage rear 

attachment fitting. This AD requires a 

detailed inspection of the upper and 

lower lugs of each horizontal stabilizerto-fuselage rear attachment fitting, 

repair if necessary, and a report of 

findings. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective October 10, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 10, 2018. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Defense and Space Services/ 

Engineering Support, Avenida de 

Arago ́n 404, 28022 Madrid, Spain; 

telephone +34 91 585 55 84; fax +34 91 

585 31 27; email: 

MTA.TechnicalService@airbus.com. 

You may view this service information 

at the FAA, Transport Standards 

Branch, 2200 South 216th St., Des 

Moines, WA. For information on the 

availability of this material at the FAA, 

call 206–231–3195. It is also available 

on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0416. 

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–2018– 

0416; or in person at Docket Operations 

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 Docket 

Operations (phone: 800–647–5527) is 

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: 

Shahram Daneshmandi, Aerospace 

Engineer, International Section, 

Transport Standards Branch, FAA, 2200 

South 216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3220. 

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 Defense and Space 

S.A. Model CN–235, CN–235–100, CN– 

235–200, and CN–235–300 airplanes; 

and certain Model C–295 airplanes. The 

NPRM published in the Federal 

Register on May 25, 2018 (83 FR 24236). 

The NPRM was prompted by a report 

that cracks were found on the stabilizerto-fuselage rear attachment fitting. The 

NPRM proposed to require a detailed 

inspection of the upper and lower lugs 

of each horizontal stabilizer-to-fuselage 

rear attachment fitting, repair if 

necessary, and a report of findings. 

We are issuing this AD to address 

such cracking, which could lead to 

reduced structural integrity of the lugs 

on the stabilizer-to-fuselage rear 

attachment fittings and consequent lug 

or fitting failure, and could result in 

reduced controllability of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2017–0218, 

dated November 8, 2017 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Defense and Space S.A. 

Model CN–235, CN–235–100, CN–235– 

200, and CN–235–300 airplanes; and 

certain Model C–295 airplanes. The 

MCAI states: 

Cracks were reportedly found on the 

stabilizer-to-fuselage rear attachment fitting 

of a CN–235 aeroplane. Subsequent 

investigation determined that the affected 

horizontal attachment fitting was a reworked 

part. 

This condition, if not detected and 

corrected, could lead to reduced structural 

integrity of lugs of the stabilizer-to-fuselage 

rear attachment fittings and consequent lug 

or fitting failure, possibly resulting in 

reduced control of the aeroplane. 

To address this potentially unsafe 

condition, Airbus Defence and Space (D&S) 

issued Alert Operators Transmission (AOT) 

AOT–C295–55–0005 and AOT–CN235–55– 

0004 to provide inspection instructions. 

For the reasons described above, this 

[EASA] AD requires a one-time detailed 

inspection (DET) of the upper and lower lugs 

of the horizontal stabilizer-to-fuselage rear 

attachment fittings on the left hand (LH) and 

right hand (RH) sides and, depending on 

findings, accomplishment of applicable 

corrective action(s) [repairs]. This [EASA] AD 

also requires reporting of all findings, 

including none. 

You may examine the MCAI in the 

AD docket on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0416. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

We received no comments on the NPRM 

or on the determination of the cost to 

the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this 

final rule 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 for 

addressing 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 

Airbus Defence and Space S.A. has 

issued Alert Operators Transmission 

(AOT) AOT–CN235–55–0004, Revision 

1, dated October 24, 2016; and AOT 

AOT–C295–55–0005, Revision 1, dated 

October 24, 2016. This service 

information describes a detailed 

inspection of the upper and lower lugs 

of each horizontal stabilizer-to-fuselage 

rear attachment fitting (left- and righthand sides), repair if necessary, and 

sending inspection results to the 

manufacturer. These documents are 

distinct since they apply to different 

airplane models. 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 14 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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45042 Federal Register / Vol. 83, No. 172 / Wednesday, September 5, 2018 / Rules and Regulations 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection ........................................................ 8 work-hours × $85 per hour = $680 ............. $0 $680 $9,520 

Reporting ......................................................... 1 work-hour × $85 per hour = $85 ................. 0 85 1,190 

We estimate the following costs to do 

any necessary repair that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need this repair: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Repair ........................................................................... 15 work-hours × $85 per hour = $1,275 ...................... $0 $1,275 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW, Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

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 transport category 

airplanes and associated appliances to 

the Director of the System Oversight 

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 

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. 

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): 

2018–18–09 Airbus Defense and Space S.A. 

(Formerly Known as Construcciones 

Aeronauticas, S.A.): Amendment 39– 

19388; Docket No. FAA–2018–0416; 

Product Identifier 2017–NM–164–AD. 

(a) Effective Date 

This AD is effective October 10, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Defense and 

Space S.A. Model airplanes, certificated in 

any category, specified in paragraphs (c)(1) 

and (c)(2) of this AD. 

(1) Model CN–235, CN–235–100, CN–235– 

200, and CN–235–300 airplanes, all 

manufacturer serial numbers (MSN). 

(2) Model C–295 airplanes, MSN 001 

through 148 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55, Horizontal stabilizer. 

(e) Reason 

This AD was prompted by a report that 

cracks were found on the stabilizer-tofuselage rear attachment fitting. We are 

issuing this AD to address such cracking, 

which could lead to reduced structural 

integrity of the lugs on the stabilizer-tofuselage rear attachment fittings and 

consequent lug or fitting failure, and could 


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Federal Register / Vol. 83, No. 172 / Wednesday, September 5, 2018 / Rules and Regulations 45043 

result in reduced controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Within the compliance times specified in 

figure 1 or figure 2 to paragraph (g) of this 

AD, as applicable, accomplish a detailed 

inspection for cracks or rework of the upper 

and lower lugs of each horizontal stabilizerto-fuselage rear attachment fitting (left- and 

right-hand sides), in accordance with the 

instructions of Airbus Defence and Space 

Alert Operators Transmission (AOT) AOT– 

CN235–55–0004, Revision 1, dated October 

24, 2016; or Airbus Defence and Space AOT 

AOT–C295–55–0005, Revision 1, dated 

October 24, 2016; as applicable. 

(h) Corrective Action 

If, during the detailed inspection required 

by paragraph (g) of this AD, any discrepancy 

(i.e., cracking or rework) is detected, as 

specified in Airbus Defence and Space AOT 

AOT–CN235–55–0004, Revision 1, dated 

October 24, 2016; or Airbus Defence and 

Space AOT AOT–C295–55–0005, Revision 1, 

dated October 24, 2016; as applicable: Before 

further flight, contact the Manager, 

International Section, Transport Standards 

Branch, FAA; or the European Aviation 

Safety Agency (EASA); or Airbus Defense 

and Space S.A.’s EASA Design Organization 

Approval (DOA), for approved repair 

instructions. If approved by the DOA, the 

approval must include the DOA-authorized 

signature. Accomplish the repair accordingly 

within the compliance time specified in 

those instructions, including any repetitive 

post-repair inspections, if applicable. 

(i) Reporting Requirement 

Submit a one-time report of the findings 

(both positive and negative) of the inspection 

required by paragraph (g) of this AD to 

Airbus Defense and Space S.A., in 

accordance with Airbus Defence and Space 

AOT AOT–CN235–55–0004, Revision 1, 

dated October 24, 2016; or Airbus Defence 

and Space AOT AOT–C295–55–0005, 

Revision 1, dated October 24, 2016; as 

applicable; at the applicable time specified in 

paragraph (i)(1) or (i)(2) of this AD. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 60 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 60 days after the effective date of this 

AD. 

(j) Parts Installation Limitations 

As of the effective date of this AD, no 

person may install, on any airplane, a 

horizontal stabilizer-to-fuselage rear 

attachment fitting, unless the part is new or 

it has been inspected in accordance with the 

instructions of Airbus Defence and Space 

AOT AOT–CN235–55–0004, Revision 1, 

dated October 24, 2016; or Airbus Defence 

and Space AOT AOT–C295–55–0005, 

Revision 1, dated October 24, 2016; as 

applicable; and no discrepancy was found. 

Before installation of the horizontal 

stabilizer-to-fuselage rear attachment fitting, 

contact the Manager, International Section, 

Transport Standards Branch, FAA; or the 

EASA; or Airbus Defense and Space S.A.’s 

EASA DOA, for approved instructions and do 


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45044 Federal Register / Vol. 83, No. 172 / Wednesday, September 5, 2018 / Rules and Regulations 

those instructions accordingly. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(k) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g), (h), and (i) of this 

AD, if those actions were performed before 

the effective date of this AD using Airbus 

Defence and Space AOT AOT–CN235–55– 

0004, dated December 22, 2015; or Airbus 

Defence and Space AOT AOT–C295–55– 

0005, December 22, 2015; as applicable. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards 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 International Section, send it 

to the attention of the person identified in 

paragraph (m)(2) of this AD. Information may 

be emailed to: 9–ANM–116-AMOCREQUESTS@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. 

(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 Section, 

Transport Standards Branch, FAA; or the 

EASA; or Airbus Defense and Space S.A.’s 

EASA DOA. If approved by the DOA, the 

approval must include the DOA-authorized 

signature. 

(3) Paperwork Reduction Act Burden 

Statement: A federal agency may not conduct 

or sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 1 hour per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave. SW, Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0218, dated November 8, 2017, for 

related information. This MCAI may be 

found in the AD docket on the internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2018–0416. 

(2) For more information about this AD, 

contact Shahram Daneshmandi, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3220. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(n) 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 Defence and Space Alert 

Operators Transmission AOT–CN235–55– 

0004, Revision 1, dated October 24, 2016. 

(ii) Airbus Defence and Space Alert 

Operators Transmission AOT–C295–55– 

0005, Revision 1, dated October 24, 2016. 

(3) For service information identified in 

this AD, contact Airbus Defense and Space 

Services/Engineering Support, Avenida de 

Arago ́n 404, 28022 Madrid, Spain; telephone 

+34 91 585 55 84; fax +34 91 585 31 27; email 

MTA.TechnicalService@airbus.com. 

(4) You may view this service information 

at the FAA, Transport Standards Branch, 

2200 South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

(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/ibrlocations.html. 

Issued in Des Moines, Washington, on 

August 23, 2018. 

James Cashdollar, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–18999 Filed 9–4–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–1122; Product 

Identifier 2012–NE–42–AD; Amendment 39– 

19385; AD 2018–18–06] 

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 superseding 

Airworthiness Directive (AD) 2013–02– 

04 for all Rolls-Royce plc (RR) RB211– 

Trent 970–84, RB211–Trent 970B–84, 

RB211–Trent 972–84, RB211–Trent 

972B–84, RB211–Trent 977–84, RB211– 

Trent 977B–84, and RB211–Trent 980– 

84 turbofan engines. AD 2013–02–04 

required on-wing inspections of lowpressure turbine (LPT) disk seal fins and 

interstage seals when post-flight review 

indicates Engine Health Monitoring 

(EHM) vibratory maintenance-alert 

limits were exceeded in flight. This AD 

requires additional criteria for the 

inspection of the stage 2, 3, and 4 LPT 

disk seal fins and interstage seals and 

removes the requirement to inspect the 

stage 5 LPT disk seal fins and interstage 

seal. This AD was prompted by a Trent 

900 engine experiencing increased lowpressure rotor vibration while in flight 

resulting in an in-flight shutdown 

(IFSD) and air turnback. We are issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective September 

20, 2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 20, 2018. 

We must receive any comments on 

this AD by October 22, 2018. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this final rule, contact Rolls-Royce plc, 

Corporate Communications, P.O. Box 

31, Derby, England, DE248BJ; phone: 

011–44–1332–242424; fax: 011–44– 

1332–245418, or email: http://

www.rolls-royce.com/contact/civil_

team.jsp. 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– 

7759. It is also available on the internet 


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