Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Rules and Regulations 46859 

398, 405, 410, 411, 413, 465, 470, 472, 474, 

475, 478, and 480 through 482 inclusive; 

certificated in any category; except airplanes 

modified in accordance with the 

Accomplishment Instructions of EADS– 

CASA Service Bulletin SB–212–27–0057, 

dated May 21, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by reports of 

failures of the rudder pedal control system 

support. We are issuing this AD to address 

failure of the rudder pedal control system, 

which could result in reduced controllability 

of the airplane. 

(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 

part is defined as a rudder pedal support box 

having Part Number (P/N) 212–46195.1 and 

shaft P/N 212–46120–20. 

(2) For the purposes of this AD, a 

discrepancy or defect of the rudder pedal 

support box P/N 212–46195.1 is defined as 

any crack or deformation on any welded area. 

(3) For the purposes of this AD, a 

discrepancy or defect of the shaft P/N 212– 

46120–20 is defined as any crack or 

deformation. 

(h) Repetitive Detailed Visual Inspections 

Within 3 months or during the next 

scheduled A-check maintenance, whichever 

occurs first after the effective date of this AD, 

and thereafter, at intervals not to exceed 150 

flight hours, do a detailed visual inspection 

of each affected part in accordance with the 

instructions of Airbus Alert Operators 

Transmission AOT–C212–27–0002, dated 

February 28, 2018. 

(i) Corrective Action for Any Discrepancy or 

Defect 

If any discrepancy or defect is detected 

during any inspection required by paragraph 

(h) of this AD: Before further flight, obtain 

corrective actions 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); and accomplish the 

corrective actions within the compliance 

time specified therein. If approved by the 

DOA, the approval must include the DOAauthorized signature. Accomplishment of a 

repair, as required by this paragraph, does 

not constitute terminating action for the 

repetitive inspections required by paragraph 

(h) of this AD. 

(j) Parts Installation Limitation 

As of the effective date of this AD, an 

affected part may be installed on any airplane 

provided that it is a new part or that, before 

installation, the visual inspection required by 

paragraph (h) of this AD has been 

accomplished on that part and the part 

passed the inspection (no discrepancy or 

defect detected), as required by paragraph (h) 

of this AD. 

(k) Terminating Action for AD 2017–19–08 

Accomplishing the actions required by this 

AD terminates all of the requirements of AD 

2017–19–08. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards Branch, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the International Section, send it 

to the attention of the person identified in 

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

be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Section, 

Transport Standards Branch, FAA; or EASA; 

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

DOA. If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2018–0051, dated March 2, 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–2018–0552. 

(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; phone and fax: 

206–231–3220. 

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Alert Operators Transmission 

AOT–C212–27–0002, dated February 28, 

2018. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus Defense and Space, 

Services/Engineering support, Avenida de 

Arago ́n 404, 28022 Madrid, Spain; phone: 

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

email: MTA.TechnicalService@

military.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 30, 2018. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2018–19756 Filed 9–14–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0448; Product 

Identifier 2017–NM–129–AD; Amendment 

39–19403; AD 2018–19–03] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Fokker Services B.V. Model F28 Mark 

0070 and 0100 airplanes. This AD was 

prompted by a report of cracks, in 

various directions, in the lower portion 

of a main landing gear (MLG) piston. 

This AD requires a detailed visual 

inspection of the MLG, and replacement 

if necessary. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective October 22, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 22, 2018. 

ADDRESSES: For service information 

identified in this final rule, contact 

Fokker Services B.V., Technical 

Services Dept., P.O. Box 1357, 2130 EL 

Hoofddorp, the Netherlands; phone: +31 

(0)88–6280–350; fax: +31 (0)88–6280– 

111; email: technicalservices@

fokker.com; internet: http://

www.myfokkerfleet.com. You may view 

this service information at the FAA, 

Transport Standards Branch, 2200 


daltland on DSKBBV9HB2PROD with RULES
46860 Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Rules and Regulations 

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– 

0448. 

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– 

0448; 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: Tom 

Rodriquez, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

phone and fax 206–231–3226. 

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 Fokker Services B.V. 

Model F28 Mark 0070 and 0100 

airplanes. The NPRM published in the 

Federal Register on May 25, 2018 (83 

FR 24233). The NPRM was prompted by 

a report of cracks, in various directions, 

in the lower portion of a MLG piston. 

The NPRM proposed to require a 

detailed visual inspection of the MLG, 

and replacement if necessary. 

We are issuing this AD to address 

cracks in the lower portion of the MLG, 

which could lead to MLG failure during 

the landing roll-out, and possibly result 

in damage to the airplane and injury to 

occupants. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2017–0163, 

dated September 4, 2017; corrected 

September 5, 2017 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Fokker Services B.V. Model 

F28 Mark 0070 and 0100 airplanes. The 

MCAI states: 

An occurrence was reported where, during 

a walk around check, a number of cracks, in 

various directions, were discovered in the 

lower portion of a MLG piston, Part Number 

(P/N) 41141–5. No technical investigation 

results are available as yet, but based on a 

previous event, as a result of which EASA 

issued AD 2009–0221R1, later superseded by 

[EASA] AD 2011–0159, stress corrosion is 

suspected to have caused these cracks. 

This condition, if not detected and 

corrected, could lead to MLG failure during 

the landing roll-out, possibly resulting in 

damage to the aeroplane and injury to 

occupants. 

To address this potential unsafe condition, 

Fokker Services published Service Bulletin 

(SB) SBF100–32–169 to provide inspection 

instructions. 

For the reasons described above, this 

[EASA] AD requires a one-time detailed 

visual inspection (DVI) of the MLG pistons 

for cracks and, depending on findings, 

replacement. 

This [EASA] AD also requires the reporting 

of inspection results to Fokker Services. 

This [EASA] AD has been republished to 

correct wrong P/N references in paragraphs 

(1) and (4). 

This [EASA] AD is considered an interim 

measure and further [EASA] AD action may 

follow. 

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– 

0448. 

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 

Fokker Services B.V. has issued 

Fokker Service Bulletin SBF100–32– 

169, dated August 23, 2017. The service 

information describes procedures for a 

detailed visual inspection of the MLG, 

and replacement if necessary. 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 5 

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 

Detailed visual inspection ............................... 3 work-hours × $85 per hour = $255 ............. $0 $255 $1,275 

Reporting ......................................................... 1 work-hour × $85 per hour = $85 ................. 0 85 425 

We estimate the following costs to do 

any necessary replacement that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need this replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

MLG Replacement ........................... 12 work-hours × $85 per hour = $1,020 ................................................... $95,000 $96,020 


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Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Rules and Regulations 46861 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW, Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to transport category 

airplanes and associated appliances to 

the Director of the System Oversight 

Division. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2018–19–03 Fokker Services B.V.: 

Amendment 39–19403; Docket No. 

FAA–2018–0448; Product Identifier 

2017–NM–129–AD. 

(a) Effective Date 

This AD is effective October 22, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F28 Mark 0070 and 0100 airplanes, 

certificated in any category, all manufacturer 

serial numbers, if equipped with Goodrich 

main landing gear (MLG). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing gear. 

(e) Reason 

This AD was prompted by a report of 

cracks, in various directions, in the lower 

portion of a MLG piston. We are issuing this 

AD to detect and correct cracks in the lower 

portion of the MLG, which could lead to 

MLG failure during the landing roll-out, and 

possibly result in damage to the airplane and 

injury to occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) One-Time Detailed Visual Inspection 

Within 30 days after the effective date of 

this AD, do a detailed visual inspection of 

each MLG piston part number (P/N) 41141– 

5, in accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–32–169, dated August 23, 2017. 

(h) Corrective Actions 

If any crack is found, during any 

inspection required by paragraph (g) of this 

AD, before further flight, replace the MLG 

piston with a serviceable piston (i.e., a new 

piston, a piston that has not accumulated any 

flight cycles since overhaul, or a piston that 

has been inspected as required by paragraph 

(g) of this AD and has no cracks), in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–32–169, dated August 23, 2017. 

(i) Reporting 

(1) Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (g) of this AD to 

Fokker Services B.V., Technical Services, fax: 

+31 (0)25–2627–211; email: 

technicalservices@fokker.com, at the 

applicable time specified in paragraph 

(i)(1)(i) or (i)(1)(ii) of this AD. The report 

must include the information specified in the 

questionnaire of Fokker Service Bulletin 

SBF100–32–169, dated August 23, 2017. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(2) Although Fokker Service Bulletin 

SBF100–32–169, dated August 23, 2017, 

specifies to submit certain information to 

Goodrich, this AD does not include that 

requirement. 

(j) Parts Installation Limitations 

As of the effective date of this AD, it is 

allowed to install a MLG piston P/N 41141– 

5, or a replacement MLG with a MLG piston 

P/N 41141–5, on any airplane, provided the 

MLG piston is new, or has not accumulated 

any flight cycles since overhaul, or has been 

inspected as required by paragraph (g) of this 

AD and has no cracks. 

(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 


daltland on DSKBBV9HB2PROD with RULES
46862 Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Rules and Regulations 

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 

European Aviation Safety Agency (EASA); or 

Fokker Services B.V.’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 1 hour per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW, Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0163, dated September 4, 2017; 

corrected September 5, 2017, for related 

information. This MCAI may be found in the 

AD docket on the internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2018–0448. 

(2) For more information about this AD, 

contact Tom Rodriquez, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 2200 South 216th St., Des 

Moines, WA 98198; phone and fax 206–231– 

3226. 

(m) 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) Fokker Service Bulletin SBF100–32– 

169, dated August 23, 2017. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 1357, 

2130 EL Hoofddorp, the Netherlands; phone: 

+31 (0)88–6280–350; fax: +31 (0)88–6280– 

111; email: technicalservices@fokker.com; 

internet: http://www.myfokkerfleet.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 30, 2018. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2018–19754 Filed 9–14–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0384; Product 

Identifier 2017–SW–061–AD; Amendment 

39–19401; AD 2018–19–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model AS–365N2, AS 365 

N3, EC 155B, EC155B1, SA–365N1, and 

SA–366G1 helicopters. This AD requires 

repetitive inspections of the aft fuselage 

outer skin. This AD was prompted by 

several reports of aft fuselage outer skin 

disbonding. The actions of this AD are 

intended to address an unsafe condition 

on these products. 

DATES: This AD is effective October 22, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of October 22, 2018. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, 2701 N Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http://

www.helicopters.airbus.com/website/ 

en/ref/Technical-Support_73.html. You 

may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy., Room 6N–321, 

Fort Worth, TX 76177. You may review 

the referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, TX 

76177. It is also available on the internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2018–0384. 

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– 

0384; 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 AD, the 

European Aviation Safety Agency 

(EASA) AD, any incorporated-byreference service information, the 

economic evaluation, any comments 

received, and other information. The 

street 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: Matt 

Fuller, Senior Aviation Safety Engineer, 

Safety Management Section, Rotorcraft 

Standards Branch, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

matthew.fuller@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 9, 2018, at 83 FR 21194, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 by 

adding an AD that would apply to 

Airbus Helicopters Model AS–365N2, 

AS 365 N3, EC 155B, EC155B1, SA– 

365N1, and SA–366G1 helicopters. 

The NPRM proposed to require a 

repetitive tap inspection of the aft 

fuselage outer skin for disbonding. 

Depending on the inspection results, the 

NPRM proposed to require reducing the 

compliance time interval of the tap 

inspections or repairing or replacing the 

panel to terminate the shorter 

compliance time interval. The NPRM 

also proposed to require a repetitive 

cleaning of the aft fuselage outer skin to 

visually inspect for distortion, 

wrinkling, and corrosion. Depending on 

the visual inspection results, the NPRM 

proposed to require an additional tap 

inspection of the area. The proposed 


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