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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Federal Register / Vol. 83, No. 178 / Thursday, September 13, 2018 / Rules and Regulations 46373 

In some areas of the Horizontal Tail Plane 

(HTP) [horizontal stabilizer] and fuselage 

Section (S) 19 [rear fuselage cone structure], 

the interfay sealant for multimaterial joints 

(hybrid joints) was only applied on the 

surface in direct contact with aluminium 

parts and not between all surfaces of the joint 

parts. This situation does not ensure full 

barrier properties. To avoid any risk of water 

ingress in multi-material-stacks involving 

aluminium, it is necessary to apply interfay 

sealant between all assembled parts, even 

between parts made of corrosion resistant 

material. This ensures a double barrier in the 

joint and prevents subsequent potential 

galvanic corrosion on the aluminum holes on 

top of the single barrier already applied in 

aluminium parts. 

This condition, if not corrected, could 

reduce the structural integrity of the HTP and 

fuselage at S19. 

To address this unsafe condition, Airbus 

developed production mod [Modification] 

106695 for fuselage at S19 and mod 107824 

for HTP to improve protection against 

corrosion, and issued [Airbus] SB [Service 

Bulletin] A350–53–P029 (Airbus mod 

110281) and [Airbus] SB A350–55–P003 

(Airbus mod 107877 and mod 108494) to 

provide modification instructions for inservice pre-mod aeroplanes. 

For the reasons described above, this 

[EASA] AD requires application of sealant 

and protective treatment on the affected areas 

of the HTP and fuselage at S19 and, for 

certain aeroplanes, modification of the 

trimmable horizontal stabilizer (THS) torsion 

box [and re-identification of the elevator]. 

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– 

0506. 

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 SAS has issued Service 

Bulletin A350–53–P029, dated 

November 17, 2017. This service 

information describes procedures to 

apply sealant and protective treatment 

on the affected areas of the rear fuselage 

cone structure. 

Airbus SAS has issued Service 

Bulletin A350–55–P003, dated 

November 6, 2017. This service 

information describes procedures to 

apply sealant and protective treatment 

on the affected areas of the horizontal 

stabilizer, modify the THS torsion box 

in zone 330 and 340, and re-identify the 

elevator in zone 335 and 345. 

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 6 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

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

operators 

Up to 57 work-hours × $85 per hour = $4,845 ............... Unavailable ........................ Up to $4,845 ...................... Up to $29,070. 

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: 


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46374 Federal Register / Vol. 83, No. 178 / Thursday, September 13, 2018 / Rules and Regulations 

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): 

2018–17–24 Airbus SAS: Amendment 39– 

19378; Docket No. FAA–2018–0506; 

Product Identifier 2018–NM–045–AD. 

(a) Effective Date 

This AD is effective October 18, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus SAS Model 

A350–941 airplanes certificated in any 

category, all manufacturer serial numbers, 

except those on which Airbus Modification 

106695 (or retrofit Modification 110281) and 

Modification 107824 (or retrofit Modification 

107877 and retrofit Modification 108494) 

have been embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage; 55, Stabilizers. 

(e) Reason 

This AD was prompted by the discovery of 

inadequate corrosion protection in certain 

areas of the horizontal stabilizer and the rear 

fuselage cone structure. We are issuing this 

AD to prevent reduced structural integrity of 

the horizontal stabilizer and the rear fuselage 

cone structure. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definitions 

(1) For the purpose of this AD, Group 1 

airplanes are those with manufacturer serial 

numbers (MSNs) listed in Section 1.A., 

‘‘Applicability’’ of Airbus Service Bulletin 

A350–53–P029, dated November 17, 2017. 

(2) For the purpose of this AD, Group 2 

airplanes are those with MSNs listed in 

Section 1.A., ‘‘Applicability’’ of Airbus 

Service Bulletin A350–55–P003, dated 

November 6, 2017. 

(h) Modification 

(1) For Group 1 airplanes: Before exceeding 

36 months since the date of issuance of the 

original standard airworthiness certificate or 

date of issuance of the original export 

certificate of airworthiness, or within 90 days 

after the effective date of this AD, whichever 

occurs later, apply sealant and protective 

treatment on the affected areas of the rear 

fuselage cone structure, as defined in, and in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A350– 

53–P029, dated November 17, 2017. 

(2) For Group 2 airplanes: Before exceeding 

36 months since the date of issuance of the 

original standard airworthiness certificate or 

date of issuance of the original export 

certificate of airworthiness, or within 90 days 

after the effective date of this AD, whichever 

occurs later, accomplish concurrently the 

actions specified in paragraphs (h)(2)(i) and 

(h)(2)(ii) of this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A350–55–P003, dated 

November 6, 2017. 

(i) Apply sealant and protective treatment 

on the affected areas of the horizontal 

stabilizer, as defined in Airbus Service 

Bulletin A350–55–P003, dated November 6, 

2017. 

(ii) Modify the trimmable horizontal 

stabilizer (THS) torsion box in zone 330 and 

340, and re-identify the elevator in zone 335 

and 345. 

(i) 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 (j)(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 SAS’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(3) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2018–0036, dated February 7, 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–2018–0506. 

(2) For more information about this AD, 

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. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A350–53–P029, 

dated November 17, 2017. 

(ii) Airbus Service Bulletin A350–55–P003, 

dated November 6, 2017. 

(3) For service information identified in 

this AD, 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. 

(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/ibr-locations.html. 

Issued in Des Moines, Washington, on 

August 17, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–19749 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–2018–0765; Product 

Identifier 2018–NM–105–AD; Amendment 

39–19379; AD 2018–17–25] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus SAS Model A350–941 and –1041 

airplanes. This AD was prompted by 

reports of uncommanded motion of the 

flight control actuator. This AD requires 

replacing certain rudder and elevator 

servocontrols with serviceable 


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