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
51176 Federal Register / Vol. 82, No. 212 / Friday, November 3, 2017 / Proposed Rules 

Counsel, Southwest Region, 10101 

Hillwood Pkwy., Room 6N–321, Fort 

Worth, TX 76177. 

FOR FURTHER INFORMATION CONTACT: Rao 

Edupuganti, Aviation Safety Engineer, 

Regulations and Policy Section, 

Rotorcraft Standards Branch, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5110; email 

rao.edupuganti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

We issued AD 2013–16–14, 

Amendment 39–17552 (78 FR 54383, 

September 4, 2013) (AD 2013–16–14) for 

Eurocopter Deutschland GmbH (now 

Airbus Helicopters Deutschland GmbH) 

Model EC135 P1, P2, P2+, T1, T2, and 

T2+ helicopters with a certain serialnumbered main transmission FS108 

housing upper part (upper part), part 

number (P/N) 4649 301 034. AD 2013– 

16–14 requires installing a corrugated 

washer in the filter housing of the upper 

part and modifying each affected upper 

part by machining the oil filter bypass 

inlet. AD 2013–16–14 was prompted by 

AD No. 2010–0213, dated October 14, 

2010, issued by EASA, which is the 

Technical Agent for the Member States 

of the European Union. EASA issued 

AD No. 2010–0213 to correct an unsafe 

condition for Eurocopter Deutschland 

GmbH Model EC 135 and EC635 

helicopters. EASA advised that a recent 

inspection on some upper parts for the 

main transmission FS108 revealed the 

bypass inlet in the oil filter area had not 

been manufactured in accordance with 

the applicable design specifications. 

EASA advised that this condition, if not 

detected and corrected, could adversely 

affect the oil-filter bypass function, 

which is essential for continued safe 

flight. The EASA AD required a 

temporary modification of the upper 

part by installing a corrugated washer, 

and then a ‘‘rework’’ of the oil filter area 

to bring the affected parts within the 

applicable design specifications. 

Actions Since AD 2013–16–14 Was 

Issued 

Since we issued AD 2013–16–14, 

EASA has issued AD 2017–0002, dated 

January 9, 2017 (AD 2017–0002), which 

superseded EASA AD 2010–0213. EASA 

advises that some affected upper parts 

have been re-identified with P/N 4649 

301 067 or P/N 4649 301 088 without 

changing the serial number. EASA 

further advises that Airbus Helicopters 

has extended the compliance time to 

retrofit the housing to 5,150 hours to 

coincide with the extended interval 

between transmission overhauls. 

Accordingly, AD 2017–002 continues to 

require installing a corrugated washer in 

the upper part and modifying the upper 

part at the next overhaul; expands the 

applicability to include Model EC135P3, 

Model EC135T3, P/N 4649 301 067, and 

P/N 4649 301 088; extends the 

compliance time for machining the 

upper part; and makes minor editorial 

changes for clarity. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, EASA, its 

technical representative, has notified us 

of the unsafe condition described in its 

AD. We are proposing this AD because 

we evaluated all known relevant 

information and determined that an 

unsafe condition is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Airbus Helicopters Alert 

Service Bulletin (ASB) EC135–63A–017, 

Revision 2, dated December 5, 2016 

(ASB EC135–63A–017), for Model 

EC135 T1, T2, T2+, T3, P1, P2, P2+, P3, 

and 635 T1, T2+, T3, P2+, and P3 

helicopters. This service information 

specifies removing the oil filter element 

and installing a corrugated washer. ASB 

EC135–63A–017 also specifies 

reworking the affected upper part at the 

next repair or overhaul of the main 

transmission, no later than 5,150 flight 

hours after receipt of the service 

bulletin. EASA classified this ASB as 

mandatory and issued AD 2017–0002 to 

ensure the continued airworthiness of 

these helicopters. 

We also reviewed ZF Luftfahrttechnik 

GmbH Service Instruction No. 

EC135FS108–1659–1009, dated 

September 14, 2010, which specifies 

procedures for repairing the main 

transmission upper housing, and 

includes dimensions and tolerances for 

machining the upper part. 

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. 

Other Related Service Information 

We reviewed Eurocopter Alert Service 

Bulletin EC135–63A–017, Revision 0, 

dated October 11, 2010, for Model 

EC135 T1, T2, T2+, P1, P2, P2+, and 635 

T1, T2+, and P2+ helicopters. This 

service information specifies the same 

Accomplishment Instructions as ASB 

EC135–63A–017, Revision 2, except 

with a shorter compliance time to 

rework the affected upper part. 

Proposed AD Requirements 

This proposed AD would retain the 

requirements of AD 2013–16–14 for 

installing a corrugated washer and 

modifying the upper part. This 

proposed AD would add Airbus 

Helicopters Deutschland Model 

EC135P3 and Model EC135T3 

helicopters to the applicability 

requirements, add upper parts P/N 4649 

301 067 and P/N 4649 301 088 to the 

applicability, revise the compliance 

time for installing a corrugated washer 

to within 50 hours time-in-service (TIS) 

or 3 months, whichever occurs earlier, 

and extend the compliance time for 

machining the upper part to 5,150 hours 

TIS. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 236 helicopters of U.S. 

Registry. Based on an average labor rate 

of $85 per work hour, we estimate that 

operators may incur the following costs 

in order to comply with this proposed 

AD. Installing the corrugated washer 

would require about .5 work hour, and 

required parts would cost about $10, for 

a cost per helicopter of about $53, and 

a cost to the U.S. operator fleet of 

$12,508. Machining the housing upper 

part would require about 5 work-hours 

and required parts would cost about 


jstallworth on DSKBBY8HB2PROD with PROPOSALS
Federal Register / Vol. 82, No. 212 / Friday, November 3, 2017 / Proposed Rules 51177 

$73, for a cost per helicopter of $498, 

and a total cost to U.S. operators of 

$117,528. Based on these figures, we 

estimate the total cost of this proposed 

AD to be $130,036 for the U.S. operator 

fleet or $551 per helicopter. 

According to Airbus Helicopters’ 

service information some of the costs of 

this proposed AD may be covered under 

warranty, thereby reducing the cost 

impact on affected persons. We do not 

control warranty coverage by Airbus 

Helicopters. Accordingly, we have 

included all 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. 

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, 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 to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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) 

2013–16–14, Amendment 39–17552 (78 

FR 54383, September 4, 2013), and 

adding the following new AD: 

Airbus Helicopters Deutschland GmbH 

(Type Certificate Previously Held by 

Eurocopter Deutschland GmbH): Docket 

No. FAA–2017–1011; Product Identifier 

2017–SW–004–AD. 

(a) Applicability 

This AD applies to Model EC135 P1, P2, 

P2+, P3, T1, T2, T2+, and T3 helicopters with 

a main transmission FS108 housing upper 

part, part number (P/N) 4649 301 034, 4649 

301 067, or 4649 301 088 and a serial number 

listed in Table 1 of Airbus Helicopters Alert 

Service Bulletin EC135–63A–017, Revision 2, 

dated December 5, 2016 (ASB EC135–63A– 

017), certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as an 

improperly manufactured bypass inlet in the 

oil filter area. This condition could adversely 

affect the oil-filter bypass function, resulting 

in failure of the main transmission and 

subsequent loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2013–16–14, 

Amendment 39–17552 (78 FR 54383, 

September 4, 2013). 

(d) Comments Due Date 

We must receive comments by January 2, 

2018. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) Within 3 months, remove the oil filter 

element and install a corrugated washer, P/ 

N 0630100377, in the middle of the filter 

housing of the housing upper part as 

depicted in Figure 2 of ASB EC135–63A–017. 

(2) Within 5,150 hours time-in-service or at 

the next main transmission repair or 

overhaul, whichever occurs first, machine 

the main transmission housing upper part in 

accordance with Annex A of ZF 

Luftfahrttechnik GmbH Service Instruction 

No. EC135FS108–1659–1009, dated 

September 14, 2010. 

(3) Do not install a main transmission 

upper part, P/N 4649 301 034, 4649 301 067, 

or 4649 301 088, on any helicopter unless it 

has been modified as required by paragraphs 

(f)(1) through (f)(2) of this AD. 

(g) Credit for Previous Actions 

Actions accomplished before the effective 

date of this AD in accordance with the 

procedures specified in Eurocopter Alert 

Service Bulletin EC135–63A–017, Revision 0, 

dated October 11, 2010, are considered 

acceptable for compliance with the 

corresponding actions specified in paragraph 

(f) of this AD. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Section, FAA, may approve AMOCs for this 

AD. Send your proposal to: Rao Edupuganti, 

Aviation Safety Engineer, Regulations and 

Policy Section, Rotorcraft Standards Branch, 

FAA, 10101 Hillwood Pkwy, Fort Worth, TX 

76177; telephone (817) 222–5110; email 9- 

ASW-FTW-AMOC-Requests@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(i) Additional Information 

(1) Eurocopter Alert Service Bulletin 

EC135–63A–017, Revision 0, dated October 

11, 2010, which is not incorporated by 

reference, contains additional information 

about the subject of this AD. For service 

information identified in this AD, 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 a copy of 

the service information at the FAA, Office of 

the Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy, Room 6N–321, Fort 

Worth, TX 76177. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2017–0002, dated January 9, 2017. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in the AD Docket. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6320 Main Rotor Gearbox. 

Issued in Fort Worth, Texas, on October 16, 

2017. 

James A. Grigg, 

Acting Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2017–23201 Filed 11–2–17; 8:45 am] 

BILLING CODE 4910–13–P 


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