Federal Register / Vol. 83, No. 178 / Thursday, September 13, 2018 / Rules and Regulations 46369 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0493; Product 

Identifier 2017–NM–141–AD; Amendment 

39–19389; AD 2018–18–10] 

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, 

CN–235–300, and C–295 airplanes. This 

AD was prompted by reports that cracks 

were found on the door mechanism 

actuator shaft assemblies of the nose 

landing gear (NLG). This AD requires 

repetitive inspections of the NLG door 

mechanism actuator shaft assemblies 

having certain part numbers, and 

corrective actions if necessary. This AD 

would also provide an optional 

terminating action for the repetitive 

inspections for Model CN–235, CN– 

235–100, CN–235–200, and CN–235– 

300 airplanes. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective October 18, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 18, 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– 

0493. 

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– 

0493; 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, CN–235–300, and C–295 

airplanes. The NPRM published in the 

Federal Register on June 4, 2018 (83 FR 

25587). The NPRM was prompted by 

reports that cracks were found on the 

door mechanism actuator shaft 

assemblies of the NLG. The NPRM 

proposed to require repetitive 

inspections of the NLG door mechanism 

actuator shaft assemblies having certain 

part numbers, and corrective actions if 

necessary. The NPRM also proposed to 

provide an optional terminating action 

for the repetitive inspections for Model 

CN–235, CN–235–100, CN–235–200, 

and CN–235–300 airplanes. We are 

issuing this AD to address such 

cracking, which could lead to an inflight NLG door opening and possibly 

result in detachment of the affected 

door, and consequent damage to, or 

reduced control 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 2017–0181, 

dated September 18, 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, CN–235–300, and C–295 airplanes. 

The MCAI states: 

Cracks were reportedly found on nose 

landing gear (NLG) door actuator shaft 

assemblies on CN–235 aeroplanes. The 

subsequent design review determined that 

combined or multiple rupture of the affected 

shaft assembly could occur, without this 

being signalised to the flight crew. 

This condition, if not detected and 

corrected, could lead to an in-flight NLG door 

opening, possibly resulting in detachment of 

the affected door, with consequent damage 

to, or reduced control of, the aeroplane and 

injury to persons on the ground. 

To address this unsafe condition, Airbus 

Defence & Space (D&S) issued Alert 

Operators Transmissions AOT–CN235–32– 

0001 Revision (Rev.) 2 and AOT–C295–32– 

0001 Rev. 2 to provide inspection 

instructions. 

For the reasons described above, this 

[EASA] AD requires repetitive detailed (DET) 

or special detailed [rototest] inspections of 

the NLG door actuator shaft assembly, as 

applicable, and, depending on findings, 

corrective actions [including replacement of 

any cracked component, or cracked NLG 

door mechanism actuator shaft assembly 

with a serviceable part]. This [EASA] AD also 

introduces a modification for CN–235 

aeroplanes as (optional) terminating action 

for the repetitive inspections as required by 

this [EASA] AD. 

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– 

0493. 

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 

Alert Operators Transmission (AOT) 

AOT–CN235–32–0001, Revision 2, 

dated October 26, 2016; and AOT AOT– 

C295–32–0001, Revision 2, dated 

October 26, 2016. This service 

information describes procedures for 

inspections for cracking of the door 

mechanism actuator shaft assemblies of 

the NLG, and corrective actions. These 

documents are distinct since they apply 

to different airplane models. 

Airbus Defence and Space has also 

issued Service Bulletin SB–235–32– 

0031C, dated September 22, 2016. This 


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46370 Federal Register / Vol. 83, No. 178 / Thursday, September 13, 2018 / Rules and Regulations 

service information describes 

procedures for modification of the NLG 

door latching mechanism. 

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: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspections ........ 21 work-hours × $85 per hour = 

$1,785 per inspection cycle.

$0 $1,785 per inspection cycle .......... $24,990 per inspection cycle. 

OPTIONAL TERMINATING ACTION

Action Labor cost Parts cost Cost per 

product 

Modification for Model CN–235 airplanes .................... 10 work-hours × $85 per hour = $850 ......................... $33,626 $34,476 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspections. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement ................................................................. 14 work-hours × $85 per hour = $1,190 ...................... $18,720 $19,910 

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): 

2018–18–10 Airbus Defense and Space S.A. 

(Formerly Known as Construcciones 

Aeronauticas, S.A.): Amendment 39– 

19389; Docket No. FAA–2018–0493; 

Product Identifier 2017–NM–141–AD. 

(a) Effective Date 

This AD is effective October 18, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus Defense and 

Space S.A. airplanes identified in paragraphs 

(c)(1) and (c)(2) of this AD, certificated in any 

category, all manufacturer serial numbers. 

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

200, and CN–235–300 airplanes. 

(2) Model C–295 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52, Doors. 


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Federal Register / Vol. 83, No. 178 / Thursday, September 13, 2018 / Rules and Regulations 46371 

(e) Reason 

This AD was prompted by reports that 

cracks were found on the door mechanism 

actuator shaft assemblies of the nose landing 

gear (NLG). We are issuing this AD to address 

such cracking, which could lead to an inflight NLG door opening and possibly result 

in detachment of the affected door, and 

consequent damage to, or reduced control of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definition of Affected NLG Door 

Mechanism Actuator Shaft Assembly 

For the purpose of this AD, an affected 

NLG door mechanism actuator shaft 

assembly has part number (P/N) 35–42311– 

00 or P/N 95–42315–00, depending on 

airplane model. 

(h) Detailed and Rototest Inspections 

(1) For any affected NLG door mechanism 

actuator shaft assembly: Before exceeding 

600 flight hours accumulated by any NLG 

door mechanism lever or cam since new, or 

within 60 flight hours after the effective date 

of this AD, whichever occurs later, on the 

NLG door mechanism actuator shaft 

assembly with the NLG actuator shaft 

installed, do a detailed inspection for 

cracking of all installed NLG door 

mechanism levers and cams, in accordance 

with the instructions in Airbus Defence and 

Space Alert Operators Transmission (AOT) 

AOT–CN235–32–0001, Revision 2, dated 

October 26, 2016; or AOT AOT–C295–32– 

0001, Revision 2, dated October 26, 2016; as 

applicable. Repeat the inspection thereafter 

at intervals not to exceed those specified in 

figure 1 to paragraph (h)(1) of this AD, 

depending on the findings or corrective 

actions completed, as specified in paragraphs 

(i)(1) and (i)(2) of this AD, after the previous 

inspection. 

FIGURE 1 TO PARAGRAPH (h)(1) OF THIS AD—REPETITIVE INSPECTION INTERVALS

Findings/Corrective action completed 

(after the previous inspection) 

Interval 

(flight hours) 

NLG door vibration observed (during previous flights) ................................................................................................................... 150 

No findings ....................................................................................................................................................................................... 300 

Damaged components replaced ...................................................................................................................................................... 300 

NLG door actuator shaft assembly replaced by new assembly ..................................................................................................... 600 

(2) For any affected NLG door mechanism 

actuator shaft assembly: Before exceeding 

1,800 flight hours accumulated by the NLG 

door shaft of the NLG door mechanism 

actuator shaft assembly since new, or within 

60 flight hours after the effective date of this 

AD, whichever occurs later, do a rototest or 

detailed inspection of the NLG door actuator 

shaft, in accordance with the instructions in 

Airbus Defence and Space AOT AOT– 

CN235–32–0001, Revision 2, dated October 

26, 2016; or AOT AOT–C295–32–0001, 

Revision 2, dated October 26, 2016; as 

applicable. Repeat the rototest or detailed 

inspection thereafter at intervals not to 

exceed those specified in figure 2 to 

paragraph (h)(2) of this AD, depending on the 

inspection method used during the most 

recent inspection. 

FIGURE 2 TO PARAGRAPH (h)(2) OF

THIS AD—REPETITIVE INSPECTION

INTERVALS

Inspection method Interval 

(flight hours) 

Rototest ............................ 900 

Detailed ............................. 600 

(i) Corrective Actions 

(1) During any detailed inspection required 

by paragraph (h)(1) of this AD, if any crack 

with a length of 18 millimeters (mm) (0.709 

inches) or more is found, or if there is more 

than one crack with a length of less than 18 

mm (0.709 inch) found, before further flight, 

replace the cracked component, or replace 

the NLG door mechanism actuator shaft 

assembly with a serviceable part, in 

accordance with the instructions of Airbus 

Defence and Space AOT AOT–CN235–32– 

0001, Revision 2, dated October 26, 2016; or 

AOT AOT–C295–32–0001, Revision 2, dated 

October 26, 2016; as applicable. 

(2) During any detailed inspection required 

by paragraph (h)(1) of this AD, if a single 

crack with a length of less than 18 mm (0.709 

inch) is found, within 5 flight cycles after the 

detailed inspection when the crack was 

found, replace any cracked component, or 

replace the NLG door mechanism actuator 

shaft assembly with a serviceable part, in 

accordance with the instructions of Airbus 

Defence and Space AOT AOT–CN235–32– 

0001, Revision 2, dated October 26, 2016; or 

AOT AOT–C295–32–0001, Revision 2, dated 

October 26, 2016; as applicable. 

(3) During any detailed or rototest 

inspection required by paragraph (h)(2) of 

this AD, if any crack is found, before further 

flight, replace the NLG door mechanism 

actuator shaft with a serviceable part, in 

accordance with the instructions of Airbus 

Defence and Space AOT AOT–CN235–32– 

0001, Revision 2, dated October 26, 2016; or 

AOT AOT–C295–32–0001, Revision 2, dated 

October 26, 2016; as applicable. 

(j) Replacement Not Terminating Action 

Accomplishment of any corrective action 

on an airplane, as required by paragraph 

(i)(1), (i)(2), or (i)(3) of this AD, as applicable, 

is not terminating action for the repetitive 

detailed or rototest inspections required by 

paragraphs (h)(1) and (h)(2) of this AD, for 

that airplane. 

(k) Optional Terminating Action 

For Model CN–235, CN–235–100, CN–235– 

200, and CN–235–300 airplanes: 

Modification of the NLG door latching 

mechanism, in accordance with the 

Accomplishment Instructions of Airbus 

Defence and Space Service Bulletin SB–235– 

32–0031C, dated September 22, 2016, is 

terminating action for the repetitive 

inspections required by paragraphs (h)(1) and 

(h)(2) of this AD, for that airplane. 

(l) Parts Installation Limitation 

As of the effective date of this AD, 

installation of an NLG door mechanism 

actuator shaft assembly having P/N 35– 

42311–00 or P/N 95–42315–00, or any of its 

components, is allowed, provided that the 

part is new; or provided that the assembly or 

the components, as applicable, has passed an 

inspection; in accordance with the 

instructions of Airbus Space and Defence 

AOT AOT–CN235–32–0001, Revision 2, 

dated October 26, 2016; or AOT AOT–C295– 

32–0001, Revision 2, dated October 26, 2016; 

as applicable. 

(m) Reporting Not Required 

Although Airbus Space and Defence AOT 

AOT–CN235–32–0001, Revision 2, dated 

October 26, 2016; and AOT AOT–C295–32– 

0001, Revision 2, dated October 26, 2016; 

both specify to submit certain information to 

the manufacturer, this AD does not include 

that requirement. 

(n) Credit for Previous Actions 

This paragraph provides credit for the 

initial inspection required by paragraph 

(h)(1) and (h)(2) of this AD, and the 

corrective actions required by paragraphs 

(i)(1), (i)(2), and (i)(3) of this AD, if those 

actions were performed before the effective 

date of this AD using the applicable service 

information identified in paragraphs (n)(1) 

through (n)(4) of this AD. 

(1) Airbus Space and Defence AOT AOT– 

CN235–32–0001, dated September 29, 2015. 

(2) Airbus Space and Defence AOT AOT– 

CN235–32–0001, Revision 1, dated February 

19, 2016. 

(3) Airbus Space and Defence AOT AOT– 

C295–32–0001, dated September 29, 2015. 

(4) Airbus Space and Defence AOT AOT– 

C295–32–0001, Revision 1, dated February 

19, 2016. 

(o) 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, 


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46372 Federal Register / Vol. 83, No. 178 / Thursday, September 13, 2018 / Rules and Regulations 

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 (p)(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 

Airbus Defense and Space S.A.’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0181, dated September 18, 2017, for 

related information, 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–2018–0493. 

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

(q) 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 AOT AOT– 

CN235–32–0001, Revision 2, dated October 

26, 2016. 

(ii) Airbus Defence and Space AOT AOT– 

C295–32–0001, Revision 2, dated October 26, 

2016. 

(iii) Airbus Defence and Space Service 

Bulletin SB–235–32–0031C, dated September 

22, 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. 2018–19183 Filed 9–12–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0506; Product 

Identifier 2018–NM–045–AD; Amendment 

39–19378; AD 2018–17–24] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

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 SAS Model A350–941 airplanes. 

This AD was prompted by the discovery 

of inadequate corrosion protection in 

certain areas of the horizontal stabilizer 

and the rear fuselage cone structure. 

This AD requires application of sealant 

and protective treatment on the affected 

areas of the horizontal stabilizer and the 

rear fuselage cone structure and, for 

certain airplanes, modification of the 

trimmable horizontal stabilizer (THS) 

torsion box and re-identification of the 

elevator. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective October 18, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 18, 2018. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus SAS, Airworthiness Office— 

EAL, Rond-Point Emile Dewoitine No: 

2, 31700 Blagnac Cedex, France; 

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

61 93 45 80; email continuedairworthiness.a350@airbus.com; 

internet http://www.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– 

0506. 

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– 

0506; 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 

Docket Operations, 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: 

Kathleen Arrigotti, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3218. 

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 SAS Model 

A350–941 airplanes. The NPRM 

published in the Federal Register on 

June 11, 2018 (83 FR 26882). The NPRM 

was prompted by the discovery of 

inadequate corrosion protection in 

certain areas of the horizontal stabilizer 

and the rear fuselage cone structure. The 

NPRM proposed to require application 

of sealant and protective treatment on 

the affected areas of the horizontal 

stabilizer and the rear fuselage cone 

structure and, for certain airplanes, 

modification of the THS torsion box and 

re-identification of the elevator. 

We are issuing this AD to address 

reduced structural integrity of the 

horizontal stabilizer and the rear 

fuselage cone structure. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2018–0036, 

dated February 7, 2018 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus SAS Model A350–941 

airplanes. The MCAI states: 


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