26882 Federal Register / Vol. 83, No. 112 / Monday, June 11, 2018 / Proposed Rules 

(j) Other Acceptable Installation Method 

Installation of an HMCA SW standard 

approved after the effective date of this AD 

is acceptable for compliance with the 

corresponding actions required by paragraph 

(h) of this AD, provided the conditions 

required by paragraphs (j)(1) and (j)(2) of this 

AD are met. 

(1) The HMCA SW standard must be 

approved by the Manager, International 

Section, Transport Standards Branch, FAA; 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(2) The installation must be accomplished 

in accordance with the modification 

instructions approved by the Manager, 

International Section, Transport Standards 

Branch, FAA; the EASA; or Airbus’s EASA 

DOA. If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(k) 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 (l)(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’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0200, dated October 10, 2017, for 

related information. You may examine the 

MCAI on the internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2018–0505. 

(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. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

continued-airworthiness.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. 

Issued in Des Moines, Washington, on May 

29, 2018. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2018–12230 Filed 6–8–18; 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] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A350–941 airplanes. This 

proposed AD was prompted by the 

discovery of inadequate corrosion 

protection in certain areas of the 

horizontal stabilizer and the rear 

fuselage cone structure. This proposed 

AD would 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 

trimmable horizontal stabilizer (THS) 

torsion box and re-identification of the 

elevator. We are proposing this AD to 

address the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by July 26, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

continued-airworthiness.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. 

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 the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2018–0506; Product Identifier 2018– 

NM–045–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this NPRM. We will consider 

all comments received by the closing 

date and may amend this NPRM based 

on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this NPRM. 

Discussion 

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 


daltland on DSKBBV9HB2PROD with PROPOSALS
Federal Register / Vol. 83, No. 112 / Monday, June 11, 2018 / Proposed Rules 26883 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A350–941 

airplanes. The MCAI states: 

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]. 

Related Service Information Under 1 

CFR Part 51 

Airbus 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 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. 

The 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. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 6 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed 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 proposed 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 proposed 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 to the Director of the 

System Oversight Division. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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. 


daltland on DSKBBV9HB2PROD with PROPOSALS
26884 Federal Register / Vol. 83, No. 112 / Monday, June 11, 2018 / Proposed Rules 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2018–0506; Product 

Identifier 2018–NM–045–AD. 

(a) Comments Due Date 

We must receive comments by July 26, 

2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus 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’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. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

continued-airworthiness.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. 

Issued in Des Moines, Washington, on May 

25, 2018. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2018–12229 Filed 6–8–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0508; Product 

Identifier 2018–NM–012–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A350–941 airplanes. This 

proposed AD was prompted by a 

determination that more restrictive 

maintenance requirements and 

airworthiness limitations are necessary. 

This proposed AD would require 

revising the maintenance or inspection 

program, as applicable, to incorporate 

new or more restrictive maintenance 

requirements and airworthiness 

limitations. We are proposing this AD to 

address the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by July 26, 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: Deliver to Mail 

address above between 9 a.m. and 5 


daltland on DSKBBV9HB2PROD with PROPOSALS