64438 Federal Register / Vol. 83, No. 241 / Monday, December 17, 2018 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0167; Product 

Identifier 2017–NM–131–AD; Amendment 

39–19530; AD 2018–25–18] 

RIN 2120–AA64 

Airworthiness Directives; ATR–GIE 

Avions de Transport Re ́gional 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

ATR–GIE Avions de Transport Re ́gional 

Model ATR42 and ATR72 airplanes. 

This AD was prompted by reports of 

cracking in main landing gear (MLG) 

universal joints (U-joints). This AD 

requires repetitive detailed inspections 

of the affected U-joints for cracks, and 

replacement if necessary. This AD also 

provides an optional terminating action 

for the repetitive inspections. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective January 22, 

2019. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 22, 2019. 

ADDRESSES: For service information 

identified in this final rule, contact 

Safran Landing Systems, Inovel Parc 

Sud—7, rue Ge ́ne ́ral Vale ́rie Andre ́, 

78140 VELIZY–VILLACOUBLAY– 

FRANCE; phone: +33 (0) 1 46 29 81 00; 

internet: www.safran-landingsystems.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– 

0167. 

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– 

0167; 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 supplemental NPRM 

(SNPRM) to amend 14 CFR part 39 by 

adding an AD that would apply to all 

ATR–GIE Avions de Transport Re ́gional 

Model ATR42 and ATR72 airplanes. 

The SNPRM published in the Federal 

Register on September 19, 2018 (83 FR 

47318). We preceded the SNPRM with 

an NPRM that published in the Federal 

Register on March 29, 2018 (83 FR 

13436). The NPRM was prompted by 

reports of cracking in MLG U-joints. The 

NPRM proposed to require repetitive 

detailed inspections of the affected Ujoints for cracks, and replacement if 

necessary. The NPRM also proposed to 

provide an optional terminating action 

for the repetitive inspections. We issued 

the SNPRM to increase the number of 

affected parts that must be inspected. 

We are issuing this AD to address 

cracking in MLG U-joints, which could 

lead to MLG structural failure and 

subsequent collapse of the MLG, 

possibly resulting in damage to the 

airplane and injury to the occupants. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2018–0080, 

dated April 11, 2018 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all ATR–GIE Avions de Transport 

Re ́gional Model ATR42 and Model 

ATR72 airplanes. The MCAI states: 

Occurrences were reported of finding 

cracks in certain MLG U-joints. Subsequent 

investigation identified a batch of affected Ujoints which have possibly been subjected to 

non-detected thermal abuse during the 

grinding process by the U-joint manufacturer 

in production, or by a maintenance 

organization during overhaul and/or repair. 

This condition, if not detected and 

corrected, could lead to MLG structural 

failure and subsequent collapse of the MLG, 

possibly resulting in damage to the aeroplane 

and injury to the occupants. 

To address this potential unsafe condition, 

SLS [Safran Landing Systems] published the 

applicable SB [service bulletin] to provide 

inspection instructions. Consequently, EASA 

issued AD 2017–0172 to require repetitive 

detailed visual inspection (DVI) of the 

affected U-joints for cracks, and, depending 

on findings, replacement. 

Since that AD was issued, SLS identified 

that certain s/n [serial numbers] of affected 

U-joints were inadvertently not included in 

the list of the original issue of the applicable 

SB. Consequently, SLS issued Revision 02 of 

the applicable SB to clarify the s/n tables of 

P/N [part number] D56805 and P/N D56805– 

2, and to add those missed s/n of affected Ujoints. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2017–0172, which is superseded, and 

includes reference to Revision 02 of the 

applicable SB. 

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– 

0167. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

The following presents the comment 

received on the SNPRM and the FAA’s 

response to that comment. 

Request To Modify Serviceable Parts 

Definition 

ATR–GIE Avions de Transport 

Re ́gional (ATR) requested that we revise 

paragraph (g)(2) of the proposed AD to 

be consistent with the applicable text of 

the MCAI. ATR stated that the 

paragraph as written could allow an old, 

never-installed part to be considered 

serviceable even though it is identified 

as an affected part in the service 

information. 

We agree to clarify the definition of 

serviceable parts. The language of the 

identified paragraph could be 

interpreted to allow certain affected 

parts, as defined in paragraph (g)(1) of 

this AD, to be installed as serviceable 

parts if they had never been previously 

installed. Our intent is to exclude 

installation of an affected part even if 

the part is new or repaired. We have 

changed the wording of paragraph (g)(2) 

of this AD accordingly. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this 

final rule with the change described 

previously and minor editorial changes. 

We have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the SNPRM for 

addressing the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 


amozie on DSK3GDR082PROD with RULES
Federal Register / Vol. 83, No. 241 / Monday, December 17, 2018 / Rules and Regulations 64439 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this final rule. 

Related Service Information Under 1 

CFR Part 51 

Safran Landing Systems has issued 

Service Bulletin 631–32–249, Revision 

2, dated February 13, 2018; Service 

Bulletin 631–32–250, Revision 2, dated 

February 13, 2018; and Service Bulletin 

631–32–251, Revision 2, dated February 

13, 2018. The service information 

describes procedures for detailed 

inspections of the affected U-joints for 

cracking, and replacement if necessary. 

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 62 

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 

Inspection ...................... 1 work-hour × $85 per hour = $85 per inspection cycle.$0 $85 per inspection 

cycle.

$5,270 per inspection 

cycle. 

We estimate the following costs to do 

any necessary on-condition actions that 

would be required based on the results 

of any required actions. We have no way 

of determining the number of aircraft 

that might need these on-condition 

actions: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement .................................... 8 work-hours × $85 per hour = $680 ........................................................ $14,083 $14,763 

According to the manufacturer, some 

or all 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 known 

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 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): 

2018–25–18 ATR–GIE Avions de Transport 

Re ́gional: Amendment 39–19530; Docket 

No. FAA–2018–0167; Product Identifier 

2017–NM–131–AD. 

(a) Effective Date 

This AD is effective January 22, 2019. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to ATR–GIE Avions de 

Transport Re ́gional Model ATR42–200, –300, 

–320, and –500 airplanes; and Model 

ATR72–101, –102, –201, –202, –211, –212, 


amozie on DSK3GDR082PROD with RULES
64440 Federal Register / Vol. 83, No. 241 / Monday, December 17, 2018 / Rules and Regulations 

and –212A airplanes; certificated in any 

category; all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing gear. 

(e) Reason 

This AD was prompted by reports of 

cracking in certain main landing gear (MLG) 

universal joints (U-joints). We are issuing this 

AD to address cracking in MLG U-joints, 

which could lead to MLG structural failure 

and subsequent collapse of the MLG, 

possibly resulting in damage to the airplane 

and injury to the occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definitions 

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

U-joint is any U-joint identified by part 

number (P/N) and serial number listed in the 

applicable service bulletin specified in 

paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of 

this AD. 

(i) For Model ATR42–200, –300, and –320 

airplanes: Safran Landing Systems Service 

Bulletin 631–32–249, Revision 2, dated 

February 13, 2018. 

(ii) For Model ATR42–500 airplanes: 

Safran Landing Systems Service Bulletin 

631–32–250, Revision 2, dated February 13, 

2018. 

(iii) For Model ATR72–101, –102, –201, 

–202, –211, –212, and –212A airplanes: 

Safran Landing Systems Service Bulletin 

631–32–251, Revision 2, dated February 13, 

2018. 

(2) For the purposes of this AD, a 

serviceable part is an affected U-joint, as 

defined in paragraph (g)(1) of this AD, 

released to service by Safran Landing 

Systems, free of defect, with the letter ‘‘V’’ 

added on the part (on the identification plate, 

or in the vicinity of the P/N marking); or any 

other U-joint with chrome-plated faces that 

were never stripped or repaired; or any other 

U-joint with chrome-plated faces that were 

stripped and repaired as specified in the 

applicable component maintenance manual 

(CMM) identified in paragraph (g)(2)(i), 

(g)(2)(ii), or (g)(2)(iii). 

(i) For Model ATR42–200, –300, and –320 

airplanes: Safran Landing Systems CMM 32– 

18–28, Rev. 10, or Safran Landing Systems 

CMM 32–18–30, Rev. 8, both dated June 2, 

2017. 

(ii) For Model ATR42–500 airplanes: 

Safran Landing Systems CMM 32–18–45, 

Rev. 5, or Safran Landing Systems CMM 32– 

18–63, Rev. 6, both dated June 2, 2017. 

(iii) For Model ATR72–101, –102, –201, 

–202, –211, –212, and –212A airplanes: 

Safran Landing Systems CMM 32–18–34, 

Rev. 9, dated June 2, 2017. 

(h) Repetitive Inspections 

Within 3 months or 500 flight cycles (FC), 

whichever occurs first, after the effective date 

of this AD, and thereafter at intervals not to 

exceed 500 FC: Do a detailed inspection for 

cracking of each affected U-joint, as 

identified in paragraph (g)(1) of this AD, in 

accordance with the Accomplishment 

Instructions of the applicable service bulletin 

specified in paragraph (g)(1)(i), (g)(1)(ii), or 

(g)(1)(iii) of this AD. 

(i) Corrective Action 

If, during any inspection required by 

paragraph (h) of this AD, any cracked U-joint 

is found, before further flight: Replace the 

cracked U-joint with a serviceable part, as 

defined in paragraph (g)(2) of this AD, in 

accordance with the Accomplishment 

Instructions of the applicable service bulletin 

specified in paragraph (g)(1)(i), (g)(1)(ii), or 

(g)(1)(iii) of this AD. 

(j) Optional Terminating Action for Required 

Repetitive Inspections 

Replacement of all affected U-joints on an 

airplane, as identified in paragraph (g)(1) of 

this AD, with serviceable parts, as defined in 

paragraph (g)(2) of this AD, constitutes 

terminating action for the repetitive 

inspections required by paragraph (h) of this 

AD for that airplane. 

(k) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install, on any airplane, an 

affected U-joint, as identified in paragraph 

(g)(1) of this AD, unless it is a serviceable 

part, as defined in paragraph (g)(2) of this 

AD. 

(l) No Reporting Requirement 

Although the Accomplishment Instructions 

of the service bulletins identified in 

paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of 

this AD specify to submit certain information 

to the manufacturer, this AD does not 

include that requirement. 

(m) Credit for Previous Actions 

This paragraph provides credit for actions 

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

if those actions were performed before the 

effective date of this AD using the applicable 

service bulletin specified in paragraph (m)(1), 

(m)(2), or (m)(3) of this AD, provided that 

affected U-joints not identified in the service 

bulletin specified in paragraph (m)(1), (m)(2), 

or (m)(3) of this AD comply with the 

requirements of paragraphs (h) and (i) of this 

AD. 

(1) Safran Landing Systems Service 

Bulletin 631–32–249, Revision 1, dated June 

26, 2017. 

(2) Safran Landing Systems Service 

Bulletin 631–32–250, Revision 1, dated June 

26, 2017. 

(3) Safran Landing Systems Service 

Bulletin 631–32–251, Revision 1, dated June 

26, 2017. 

(n) 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 (o)(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 

European Aviation Safety Agency (EASA); or 

ATR–GIE Avions de Transport Re ́gional’s 

EASA Design Organization Approval (DOA). 

If approved by the DOA, the approval must 

include the DOA-authorized signature. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2018–0080, dated April 11, 2018, 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–2018–0167. 

(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 (p)(3) and (p)(4) of this AD. 

(p) 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) Safran Landing Systems Service Bulletin 

631–32–249, Revision 2, dated February 13, 

2018. 

(ii) Safran Landing Systems Service 

Bulletin 631–32–250, Revision 2, dated 

February 13, 2018. 

(iii) Safran Landing Systems Service 

Bulletin 631–32–251, Revision 2, dated 

February 13, 2018. 

(3) For service information identified in 

this AD, contact Safran Landing Systems, 

Inovel Parc Sud—7, rue Ge ́ne ́ral Vale ́rie 

Andre ́, 78140 VELIZY–VILLACOUBLAY– 

FRANCE; phone: +33 (0) 1 46 29 81 00; 

internet: www.safran-landing-systems.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. 


amozie on DSK3GDR082PROD with RULES
Federal Register / Vol. 83, No. 241 / Monday, December 17, 2018 / Rules and Regulations 64441 

Issued in Des Moines, Washington, on 

December 6, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–27130 Filed 12–14–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0805; Product 

Identifier 2018–NM–103–AD; Amendment 

39–19527; AD 2018–25–16] 

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 certain 

Airbus Defense and Space S.A. Model 

CN–235, CN–235–200 and CN–235–300 

airplanes. This AD was prompted by a 

determination that new or more 

restrictive airworthiness limitations are 

necessary. This AD requires revising the 

maintenance or inspection program, as 

applicable, to incorporate new or more 

restrictive airworthiness limitations. We 

are issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective January 22, 

2019. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 22, 2019. 

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– 

0805. 

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– 

0805; 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 certain Airbus Defense and 

Space S.A. Model CN–235, CN–235–200 

and CN–235–300 airplanes. The NPRM 

published in the Federal Register on 

October 9, 2018 (83 FR 50539). The 

NPRM was prompted by a 

determination that new or more 

restrictive airworthiness limitations are 

necessary. The NPRM proposed to 

require revising the maintenance or 

inspection program, as applicable, to 

incorporate new or more restrictive 

airworthiness limitations. 

We are issuing this AD to address 

fatigue cracking, damage, and corrosion 

in principal structural elements; such 

fatigue cracking, damage, and corrosion 

could result in reduced structural 

integrity 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 2018–0134, 

dated June 25, 2018 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Defense and Space 

S.A. Model CN–235, CN–235–200, and 

CN–235–300 airplanes. The MCAI 

states: 

The airworthiness limitations and/or 

certification maintenance instructions for the 

EADS–CASA CN–235 aeroplanes, which are 

approved by EASA, are currently defined and 

published in the Airbus D&S CN–235 ALL 

[Airworthiness Limitations List] DT–86–3001 

document. These instructions have been 

identified as mandatory for continued 

airworthiness. 

Failure to accomplish these instructions 

could result in an unsafe condition [i.e., 

fatigue cracking, damage, and corrosion in 

principal structural elements, which could 

result in reduced structural integrity of the 

airplane]. 

For the reason described above, this 

[EASA] AD requires accomplishment of the 

actions specified in the ALL. 

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– 

0805. 

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 has issued 

Technical Document DT–86–3001, CN– 

235 Airworthiness Limitations List, 

Issue R, dated March 20, 2018. This 

service information describes 

airworthiness limitations for airplane 

systems, structural inspections, safe life 

structural items, and safe life system 

items. 

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 9 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

We have determined that revising the 

maintenance or inspection program 

takes an average of 90 work-hours per 

operator, although we recognize that 

this number may vary from operator to 

operator. In the past, we have estimated 

that this action takes 1 work-hour per 

airplane. Since operators incorporate 

maintenance or inspection program 

changes for their affected fleet(s), we 


amozie on DSK3GDR082PROD with RULES