51172 Federal Register / Vol. 82, No. 212 / Friday, November 3, 2017 / Proposed Rules 

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 engines, propellers, and 

associated appliances to the Manager, 

Engine and Propeller Standards Branch, 

Policy and Innovation 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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Safran Helicopter Engines, S.A. (Type 

Certificate previously held by 

Turbomeca, S.A): Docket No. FAA– 

2017–0838; Product Identifier 2017–NE– 

33–AD. 

(a) Comments Due Date 

We must receive comments by December 

18, 2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Safran Helicopter 

Engines S.A. Arriel 2E turboshaft engines 

with front support, part number 0 292 11 715 

0, installed (pre-mod TU 197 configuration). 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 8300, Accessory Gearboxes. 

(e) Reason 

This AD was prompted by reports of 

ruptured front support pins on the accessory 

gearbox front support. We are issuing this AD 

to prevent failure of a front support, loss of 

engine thrust control and reduced control of 

the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Before the accessory gearbox and 

transmission shaft module (Module 01) 

accumulates 1,600 engine operating hours 

since new, or within 80 engine operating 

hours after the effective date of this AD, 

whichever occurs later, replace the front 

support with a part eligible for installation. 

(h) Definition 

For the purpose of this AD, a part eligible 

for installation is a Module 01 with a premod TU 197 front support, that has not 

accumulated more than 1,680 engine 

operating hours since new; or a Module 01 

with a post-mod TU 197 front support. 

(i) Installation Prohibition 

As of the effective date of this AD, you may 

not install a pre-mod TU 197 front support 

on any engine with a post-mod TU 197 front 

support installed. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, FAA, ECO Branch, 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 manager of the ECO Branch, send it to 

the attention of the person identified in 

paragraph (k)(1) of this AD. You may email 

your request to: ANE-AD-AMOC@faa.gov. 

(2) 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. 

(k) Related Information 

(1) For more information about this AD, 

contact Robert Green, Aerospace Engineer, 

ECO Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7754; fax: 781–238–7199; email: 

robert.green@faa.gov. 

(2) Refer to MCAI EASA AD 2016–0235, 

dated November 24, 2016, for more 

information. You may examine the MCAI in 

the AD docket on the Internet at http://

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2017–0838. 

Issued in Burlington, Massachusetts, on 

October 24, 2017. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2017–23606 Filed 11–2–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0906; Product 

Identifier 2017–NM–039–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2005–12– 

16, for all Fokker Services B.V. Model 

F28 Mark 0100 airplanes. AD 2005–12– 

16 requires an inspection to determine 

the part number of the passenger service 

unit (PSU) panels for the PSU 

modification status, and corrective 

actions if applicable. Since we issued 

AD 2005–12–16, we have determined 

that the required modification actions 

might not have been implemented 

correctly. This proposed AD would 

require an inspection of the PSU panels 

and the PSU panel/airplane interface 

connectors for discrepancies, and 

corrective actions if necessary. This 

proposed AD would also remove 

airplanes from the applicability. We are 

proposing this AD to address the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by December 18, 

2017. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 


jstallworth on DSKBBY8HB2PROD with PROPOSALS
Federal Register / Vol. 82, No. 212 / Friday, November 3, 2017 / Proposed Rules 51173 

• 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 Fokker Services 

B.V., Technical Services Dept., P.O. Box 

1357, 2130 EL Hoofddorp, the 

Netherlands; telephone +31 (0)88–6280– 

350; fax +31 (0)88–6280–111; email 

technicalservices@fokker.com; Internet 

http://www.myfokkerfleet.com. You may 

view this referenced service information 

at the FAA, Transport Standards 

Branch, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability 

of this material at the FAA, call 425– 

227–1221. 

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–2017– 

0906; 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 proposed AD, 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: Tom 

Rodriguez, Aerospace Engineer, 

International Section, Transport 

Standards Branch, 1601 Lind Avenue 

SW., Renton, WA 98055–4056; 

telephone 425–227–1137; fax 425–227– 

1149. 

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– 

2017–0906; Product Identifier 2017– 

NM–039–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD 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 proposed AD. 

Discussion 

We issued AD 2005–12–16, 

Amendment 39–14132 (70 FR 34642, 

June 15, 2005) (‘‘AD 2005–12–16’’), for 

all Fokker Services B.V. Model F28 

Mark 0100 airplanes. AD 2005–12–16 

was prompted by reports of smoke in 

the passenger compartment during 

flight. One of those incidents also 

included a burning smell and 

consequently led to emergency 

evacuation of the airplane. AD 2005– 

12–16 requires an inspection to 

determine the part number of the PSU 

panels for the PSU modification status, 

and corrective actions if applicable. We 

issued AD 2005–12–16 to detect and 

correct overheating of the PSU panel 

due to moisture ingress, which could 

result in smoke or fire in the passenger 

cabin. 

Since we issued AD 2005–12–16, we 

have determined that the modification 

actions required by AD 2005–12–16 

might not have been implemented 

correctly. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2017–0043, dated March 15, 

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 0100 

airplanes. The MCAI states: 

Reports were received of burning smell and 

smoke in the passenger compartment during 

flight as a result of overheating of passenger 

service units (PSU). These were attributed to 

moisture ingress into the interface electrical 

connectors of an unsealed PSU panel. 

This condition, if not detected and 

corrected, could lead to further incidents of 

smoke in the passenger compartment, 

possibly resulting in injury to occupants. 

To address this potential unsafe condition, 

Grimes Aerospace Company, the PSU 

manufacturer (currently Honeywell) issued 

SB 10–1178–33–0040 and SB 10–1571–33– 

0041, and Fokker Services issued SBF100– 

25–097, to provide instructions for 

installation of improved sealing of the PSU 

and its interface electrical connectors. 

Subsequently, CAA–NL [Civil Aviation 

Authority—The Netherlands] issued AD 

(BLA) 2004–022 [which corresponds to FAA 

AD 2005–12–16] to require modification, 

cleaning and sealing of the affected PSU. 

Since that [CAA–NL] AD was issued, 

following a new occurrence of burning smell 

and smoke in the passenger compartment 

during disembarking of the passengers, the 

investigation revealed that, on several 

aeroplanes, the modification instructions of 

Honeywell and Fokker Services (SB listed 

above) were not, or not correctly, 

implemented. Prompted by these findings, 

Fokker Services published SBF100–25–128, 

providing inspection instructions to detect 

non-accomplishment and any discrepancy 

with the original modification instructions. 

For the reasons described above, this 

[EASA] AD retains the requirement of CAA– 

NL AD (BLA) 2004–022, which is 

superseded, and requires a one-time 

inspection [for discrepancies] of the PSU 

panels and their interface with the aeroplane, 

and, depending on findings, the 

accomplishment of applicable corrective 

action(s). 

Discrepancies include incorrect 

application of the sealant on the PSU 

panels, uninstalled gaskets, inability to 

properly lock the connectors, and 

incorrectly applied sealant on the 

connectors. Corrective actions include 

restoring the sealing of the affected PSU 

panel, repairing the PSU panel, or 

installing a new PSU panel with a 

replaced receptacle, and installing 

gaskets; making sure the connecter can 

properly lock; and applying sealant on 

the connector. 

The MCAI also revised the 

applicability by specifying specific line 

numbers and excluding airplanes on 

which certain modifications were done. 

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–2017– 

0906. 

Related Service Information Under 1 

CFR Part 51 

Fokker Services B.V. has issued 

Fokker Service Bulletin SBF100–25– 

128, dated July 21, 2016. This service 

information describes procedures for 

inspection of the PSU panels and the 

PSU panel/airplane interface connectors 

for discrepancies, and for incorrectly 

applied sealant on the connectors, and 

corrective actions. 

Grimes Aerospace has issued Service 

Bulletin 10–1178–33–0040, dated 

October 15, 1993; Service Bulletin 10– 

1178–33–0040, Revision 1, dated March 

25, 1996; and Service Bulletin 10–1571– 

33–0041, dated October 15, 1993. This 

service information describes 

procedures for inspection of the PSU 

panels and the PSU panel/airplane 

interface connectors for discrepancies, 

and corrective actions. This service 

information is distinct since it applies to 

different part numbers. 

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. 


jstallworth on DSKBBY8HB2PROD with PROPOSALS
51174 Federal Register / Vol. 82, No. 212 / Friday, November 3, 2017 / Proposed Rules 

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 design. 

Costs of Compliance 

We estimate that this proposed AD 

affects 8 airplanes of U.S. registry. 

The actions required by AD 2005–12– 

16, and retained in this proposed AD 

take about 5 work-hours per product, at 

an average labor rate of $85 per workhour. Required parts cost about $6 per 

product. Based on these figures, the 

estimated cost of the actions that are 

required by AD 2005–12–16 is $431 per 

product. 

We also estimate that it would take 

about 13 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $8,840, or $1,105 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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 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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2005–12–16, Amendment 39–14132 (70 

FR 34642, June 15, 2005), and adding 

the following new AD: 

Fokker Services B.V.: Docket No. FAA– 

2017–0906; Product Identifier 2017– 

NM–039–AD. 

(a) Comments Due Date 

We must receive comments by December 

18, 2017. 

(b) Affected ADs 

This AD replaces 2005–12–16, Amendment 

39–14132 (70 FR 34642, June 15, 2005) (‘‘AD 

2005–12–16’’). 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F28 Mark 0100 airplanes, certificated 

in any category, serial numbers 11244 

through 11527 inclusive, except those 

airplanes modified in service as specified in 

Fokker Service Bulletin SBF100–25–070, or 

Fokker Service Bulletin SBF100–25–109, or 

Fokker Modification Report FS–N545 or FS– 

N571. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/furnishings. 

(e) Reason 

This AD was prompted by reports of smoke 

in the passenger compartment during ground 

operations and in-flight. We are issuing this 

AD to detect and correct overheating of the 

passenger service unit (PSU) panel due to 

moisture ingress, which could result in 

smoke or fire in the passenger cabin. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection and Corrective 

Actions, With No Changes 

This paragraph restates the requirements of 

paragraph (f) of AD 2005–12–16, with no 

changes. Within 36 months after July 20, 

2005 (the effective date of AD 2005–12–16), 

inspect to determine if Grimes Aerospace 

PSU panels having part number (P/N) 10– 

1178–( ) or P/N 10–1571–( ) are installed and 

the PSU modification status if applicable, 

and do any corrective actions if applicable, 

by doing all of the actions specified in the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–25–097, dated 

December 30, 2003. 

Note 1 to paragraph (g) of this AD: Fokker 

Service Bulletin SBF100–25–097, dated 

December 30, 2003, refers to Grimes 

Aerospace Service Bulletin 10–1178–33– 

0040, Revision 1, dated March 25, 1996 (for 

PSU panels having P/N 10–1178–( )); and 

Service Bulletin 10–1571–33–0041, dated 

October 15, 1993 (for PSU panels having P/ 

N 10–1571–( )), as additional guidance for 

modifying the PSU panel. 

(h) Retained Parts Installation Limitation, 

With No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2005–12–16, with no 

changes. As of July 20, 2005 (the effective 

date of AD 2005–12–16), no person may 

install a PSU panel having P/N 10–1178–( ) 

or P/N 10–1571–( ) on any airplane, unless it 

has been inspected and any applicable 

corrective actions have been done in 

accordance with paragraph (g) of this AD. 

(i) New Affected PSU Identification 

For the purpose of this AD, Grimes 

(Honeywell) PSUs having P/N 10–1178– 

(series) with a serial number below 4000, and 


jstallworth on DSKBBY8HB2PROD with PROPOSALS
Federal Register / Vol. 82, No. 212 / Friday, November 3, 2017 / Proposed Rules 51175 

PSUs having P/N 10–1571–(series) with a 

serial number below 1000, are referred to as 

affected PSUs in paragraphs (j) through (l) of 

this AD. 

(j) New Inspections 

Within 24 months after the effective date 

of this AD: Do the actions required by 

paragraphs (j)(1) and (j)(2) of this AD. 

(1) Do a general visual inspection of the 

panel of each affected PSU for incorrect 

application of the sealant, in accordance with 

the Accomplishment Instructions of Fokker 

Service Bulletin SBF100–25–097, dated 

December 30, 2003; and, as applicable, 

Grimes Aerospace Service Bulletin 10–1178– 

33–0040, dated October 15, 1993 (for PSUs 

having P/N 10–1178–(series)); Revision 1, 

dated March 25, 1996 (for PSUs having P/N 

10–1178–(series)); and Grimes Aerospace 

Service Bulletin 10–1571–33–0041, dated 

October 15, 1993 (for PSUs having P/N 10– 

1571–(series)). 

(2) Do a general visual inspection of the 

electrical connectors of each affected PSU 

panel for discrepancies; i.e., uninstalled 

gaskets, inability to properly lock the 

connectors, and incorrectly applied sealant 

on the connectors; in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–25–128, dated July 

21, 2016. 

(k) Corrective Actions 

If, during any inspection required by 

paragraph (j) of this AD, any discrepancy is 

found, before further flight, restore the 

sealing of the affected PSU panels and 

accomplish all applicable corrective actions 

to correct the PSU panel interface, in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–25–128, dated July 21, 2016. Do all 

applicable corrective actions before further 

flight. 

(l) Parts Installation Limitation 

As of the effective date of this AD, an 

affected PSU panel may be installed on any 

airplane, provided that, before further flight 

after installation, it has been inspected in 

accordance with paragraph (j) of this AD and 

all applicable corrective actions have been 

done in accordance with paragraph (k) of this 

AD. 

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

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

(i) 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. 

(ii) AMOCs approved previously for AD 

2005–12–16 are approved as AMOCs for the 

corresponding provisions of this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, 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 Design Organization Approval 

(DOA). If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2017–0043, dated 

March 6, 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– 

2017–0906. 

(2) For more information about this AD, 

contact Tom Rodriguez, Aerospace Engineer, 

International Section, Transport Standards 

Branch, 1601 Lind Avenue SW., Renton, WA 

98055–4056; telephone 425–227–1137; fax 

425–227–1149. 

(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; 

telephone +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, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on October 

11, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–22558 Filed 11–2–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–1011; Product 

Identifier 2017–SW–004–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH (Type 

Certificate Previously Held by 

Eurocopter Deutschland GmbH) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2013–16– 

14 for Eurocopter Deutschland GmbH 

(now Airbus Helicopters Deutschland 

GmbH) Model EC 135 P1, P2, P2+, T1, 

T2, and T2+ helicopters. AD 2013–16– 

14 currently requires installing a washer 

in and modifying the main transmission 

filter housing upper part. Since we 

issued AD 2013–16–14, Airbus 

Helicopters Deutschland GmbH has 

extended the overhaul interval for the 

main transmission and determined that 

other models may have the same unsafe 

condition. This proposed AD would 

retain the requirements of AD 2013–16– 

14, add models to the applicability, and 

revise the required compliance time for 

the modification. The actions of this 

proposed AD are intended to correct an 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by January 2, 2018. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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–2017– 

1011; or in person at the Docket 

Operations Office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this proposed AD, the 

European Aviation Safety Agency 

(EASA) AD, the economic 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 service information identified in 

this proposed 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.airbushelicopters.com/website/ 

technical-expert/. 

You may review service information 

at the FAA, Office of the Regional 


jstallworth on DSKBBY8HB2PROD with PROPOSALS