54380 Federal Register / Vol. 78, No. 171 / Wednesday, September 4, 2013 / Rules and Regulations 

Engineering—SEEL5, Flight Control Systems 

A320 Family, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; fax +33 5 61 

93 44 25. The report must include the 

information specified in Appendix 01 of 

Airbus Service Bulletin A320–27–1214. 

(1) If the inspection was done on or after 

the effective date of this AD: Within 90 days 

after that inspection. 

(2) If the inspection was done before the 

effective date of this AD: Within 90 days after 

the effective date of this AD. 

(l) Parts Installation Limitations 

As of the effective date of this AD, no 

person may install a THSA having P/N 

47145–XXX (where XXX stands for any 

numerical value) on any airplane, unless that 

THSA meets the applicable criteria specified 

in paragraph (l)(1) or (l)(2) of this AD. 

(1) The THSA must not have accumulated 

20 years or more since the THSA’s first flight, 

and after installation must be inspected as 

required by paragraph (h) of this AD, at the 

later of the times specified in paragraphs 

(h)(1) and (h)(2) of this AD, and be inspected 

thereafter at intervals not to exceed 24 

months as required by paragraph (h) of this 

AD; and any applicable actions specified in 

paragraph (i) of this AD must be 

accomplished. 

(2) If the THSA has accumulated 20 years 

or more since the THSA’s first flight, it must 

have been inspected before installation as 

required by paragraph (h) of this AD and 

determined to have Type I corrosion (if the 

screw shaft lower splines thread condition 

does not meet the Type II or Type III 

condition), and be inspected thereafter at 

intervals not to exceed 24 months as required 

by paragraph (h) of this AD; and any 

applicable actions specified in paragraph (i) 

of this AD must be accomplished. 

(m) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (h) and (i) of this AD, 

if those actions were performed before the 

effective date of this AD using Goodrich 

Service Bulletin 47145–27–16, dated 

November 7, 2011; or Revision 1, dated 

August 1, 2012. 

(n) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1405; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(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 5 minutes 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. 

(o) Special Flight Permits 

Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the airplane can be 

modified (if the operator elects to do so), 

provided that, if any THSA corrosion is 

found during any action required by 

paragraph (h) of this AD, that corrosion is 

classified as Type I or Type II, as defined in 

Goodrich Service Bulletin 47145–27–16, 

dated November 7, 2011; Revision 1, dated 

August 1, 2012; or Revision 2, dated January 

27, 2013. 

(p) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information European 

Aviation Safety Agency Airworthiness 

Directive 2012–0175, dated September 7, 

2012, for related information, which can be 

found in the AD docket on the Internet at 

http://www.regulations.gov. 

(q) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Airbus Service Bulletin A320–27–1214, 

including Appendix 01, dated February 23, 

2012. 

(ii) Goodrich Service Bulletin 47145–27– 

16, dated November 7, 2011. 

(iii) Goodrich Service Bulletin 47145–27– 

16, Revision 1, dated August 1, 2012. Pages 

1 through 4 of this document are identified 

as Revision 1, dated August 1, 2012. Pages 5 

through 117 of this document are dated 

November 7, 2011. 

(iv) Goodrich Service Bulletin 47145–27– 

16, Revision 2, dated January 7, 2013. Pages 

1, 2, and 4 of this document are identified 

as Revision 1, dated August 1, 2012. Page 3 

of this document is identified as Revision 2, 

dated January 7, 2013. Pages 5 through 117 

of this document are dated November 7, 

2011. 

(3) For Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax +33 

5 61 93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

For Goodrich service information identified 

in this AD, contact Goodrich Corporation, 

Actuation Systems, Stafford Road, 

Fordhouses, Wolverhampton WV10 7EH, 

England; telephone +44 (0) 1902 624938; fax 

+44 (0) 1902 788100; email 

techpubs.wolverhampton@goodrich.com; 

Internet http://www.goodrich.com/TechPubs. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(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 Renton, Washington, on August 

23, 2013. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–21071 Filed 9–3–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0240; Directorate 

Identifier 2011–SW–060–AD; Amendment 

39–17565; AD 2013–17–01] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Eurocopter France (Eurocopter) Model 

AS350 and AS355 helicopters. This AD 


sroberts on DSK5SPTVN1PROD with RULES
Federal Register / Vol. 78, No. 171 / Wednesday, September 4, 2013 / Rules and Regulations 54381 

requires inspecting the tail rotor control 

stop screws to determine if they are 

correctly aligned and adjusting the 

screws if they are misaligned. This AD 

is prompted by the discovery of a loose 

nut on the tail rotor control stop and a 

misaligned tail rotor control stop screw. 

The actions of this AD are intended to 

detect a loose nut or a misaligned stop 

screw, which, if not corrected, could 

limit yaw authority, and consequently, 

result in a loss of helicopter control. 

DATES: This AD is effective October 9, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of October 9, 2013. 

ADDRESSES: For service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

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

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

www.eurocopter.com/techpub. You may 

review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov 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 AD, the foreign 

authority’s AD, any incorporated-byreference service information, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (phone: 800–647–5527) is U.S. 

Department of Transportation, Docket 

Operations Office, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Matt 

Fuller, Aviation Safety Engineer, 

Continued Operational Safety, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone 817–222–5110; email 

matthew.fuller@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On March 14, 2013, at 78 FR 16200, 

the Federal Register published our 

notice of proposed rulemaking (NPRM), 

which proposed to amend 14 CFR part 

39 to include an AD that would apply 

to Eurocopter Model AS350B, 

AS350BA, AS350B1, AS350B2, 

AS350C, AS350D, AS350D1, AS355E, 

AS355F, AS355F1, and AS355F2 

helicopters with an autopilot installed; 

Model AS350B3 helicopters with an 

autopilot or modification 073252 

installed; and Model AS355N and 

AS355NP helicopters with an autopilot 

or modification 071908 installed. The 

NPRM proposed to require inspecting 

the tail rotor control stop screws to 

determine if they are correctly aligned 

and adjusting the screws if they are 

misaligned. The proposed requirements 

were intended to detect a loose nut or 

a misaligned stop screw, which, if not 

corrected, could limit yaw authority, 

and consequently, result in a loss of 

helicopter control. 

The NPRM was prompted by AD No. 

2011–0164, dated August 31, 2011, 

issued by the European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Union. EASA issued AD No. 

2011–0164 to correct an unsafe 

condition for Eurocopter Model 

AS350B, AS350BA, AS350BB, 

AS350B1, AS350B2, AS350B3, AS350D, 

AS355E, AS355F, AS355F1, AS355F2, 

AS355N, and AS355NP helicopters with 

either an autopilot or certain 

modifications installed. EASA advises 

that during take-off with a sling load, 

the pilot of a Model AS350B3 helicopter 

reached one of the yaw stops before its 

usual position. The inspection that 

followed revealed that a tail rotor 

control stop nut was loose and that the 

corresponding tail rotor control stop 

screw was ‘‘out of adjustment.’’ EASA 

states that this condition, if not detected 

and corrected, ‘‘can lead to the loss of 

adjustment of the affected stop and 

consequently limit yaw authority, 

possibly resulting in loss of control of 

the helicopter.’’ 

Comments 

After our NPRM (78 FR 16200, March 

14, 2013), was published, we received 

comments from one commenter. 

Request 

The commenter suggested that an AD 

is unnecessary because operators should 

have already tightened the screw. 

We disagree that an AD is not needed. 

More than one tightening of a screw is 

necessary to correct this unsafe 

condition. This AD also requires 

monitoring the stop screws through 

repetitive inspections to determine 

whether a screw has become loose. 

Without these inspections, if a screw 

becomes loose and is not corrected, yaw 

authority could be limited, resulting in 

loss of helicopter control. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA, reviewed the 

relevant information, considered the 

comment received, and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Differences Between this AD and the 

EASA AD 

The EASA AD requires contacting 

Eurocopter under certain conditions. 

This does AD not. The EASA AD 

applies to Eurocopter Model AS350BB 

helicopters. This AD does not because 

Model AS350BB does not have an FAA 

type certificate. However, this AD 

applies to Eurocopter Model AS350C 

and AS350D1 helicopters because they 

have an FAA type certificate and 

because they have similar tail rotor stop 

screw assemblies as the other applicable 

helicopter models. The EASA AD does 

not apply to the Model AS350C and 

AS350D1 helicopters. 

Interim Action 

We consider this AD to be an interim 

action because Eurocopter is developing 

a modification to address the unsafe 

condition identified in this AD. After 

this modification is developed, 

approved, and available, we might 

consider additional rulemaking. 

Related Service Information 

Eurocopter has issued Alert Service 

Bulletin (ASB) No. AS350–05.00.64 for 

Model AS350B, BA, BB, B1, B2, B3, and 

D civil helicopters and Model AS350L1 

military helicopters, and ASB No. 

AS355–05.00.59 for Model AS355E, F, 

F1, F2, N, and NP civil helicopters, both 

Revision 0 and both dated August 30, 

2011. The ASBs specify inspecting the 

locking of the stop screws and, if 

warranted, adjusting the stops, marking 

the screw/nut assembly with a red line 

of paint, and periodically inspecting the 

paint line’s alignment on the screw/nut 

assembly. 

Costs of Compliance 

We estimate that this AD will affect 

911 helicopters of U.S. Registry and that 

labor costs average $85 per work-hour. 


sroberts on DSK5SPTVN1PROD with RULES
54382 Federal Register / Vol. 78, No. 171 / Wednesday, September 4, 2013 / Rules and Regulations 

Based on these estimates, we expect the 

following costs: 

• Inspecting the locking of the stop 

screws takes about a 0.4 work-hour for 

a labor cost of about $34 per helicopter 

and $30,974 for the U.S. fleet. No parts 

are needed. 

• Adjusting the stop screws, if 

needed, requires about a 0.2 work-hour 

for a labor cost of $17. No parts are 

needed. 

• Painting the line requires a 0.1 

work-hour for a labor cost of about $9 

per helicopter and $8,199 for the U.S. 

fleet. No parts are needed. 

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 

helicopters identified in this rulemaking 

action. 

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 

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 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. 

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): 

2013–17–01 Eurocopter France 

Helicopters: Amendment 39–17565; Docket 

No. FAA–2013–0240; Directorate Identifier 

2011–SW–060–AD. 

(a) Applicability 

This AD applies to the following 

helicopters, certificated in any category: 

(1) Model AS350B, AS350BA, AS350B1, 

AS350B2, AS350C, AS350D, AS350D1, 

AS355E, AS355F, AS355F1, and AS355F2 

helicopters with an autopilot installed; 

(2) Model AS350B3 helicopters with an 

autopilot or modification 073252 installed; 

and 

(3) Model AS355N and AS355NP 

helicopters with an autopilot or modification 

071908 installed. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

loose nut or misaligned tail rotor control stop 

screw (stop screw). This condition could 

result in limited yaw authority and 

subsequent loss of helicopter control. 

(c) Effective Date 

This AD becomes effective October 9, 2013. 

(d) 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. 

(e) Required Actions 

(1) Within 110 hours time-in-service (TIS), 

inspect the locking of the stop screws to 

determine whether the stop screws turn. 

(i) If any stop screw turns, adjust the stop 

screw. 

(ii) Mark a line of red paint on the screwnut assembly as depicted in Section B–B, 

Figure 1 of Eurocopter Alert Service Bulletin 

(ASB) No. AS350–05.00.64 or ASB No. 

AS355–05.00.59, as applicable to your model 

helicopter. Both ASBs are Revision 0 and 

dated August 30, 2011. 

(2) Thereafter, at intervals not to exceed 

110 hours TIS, inspect the stop screws to 

determine whether the paint lines on the 

screw and the nut are aligned. If the red paint 

lines are not aligned, remove the paint, adjust 

the stop screw, and mark a new line of paint 

on the screw-nut assembly as depicted in 

Section B–B, Figure 1 of Eurocopter ASB No. 

AS350–05.00.64 or ASB No. AS355–05.00.59, 

as applicable to your model helicopter. Both 

ASBs are Revision 0 and dated August 30, 

2011. 

(f) Special Flight Permits 

A one-time flight permit may be granted, 

provided that the pilot has full yaw authority 

before flight. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Fuller, 

Aviation Safety Engineer, Continued 

Operational Safety, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone 817–222–5110; email 

matthew.fuller@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. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2011–0164, dated August 31, 2011. You 

may view the EASA AD in the AD Docket on 

the Internet at http://www.regulations.gov. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6720, tail rotor control system. 

(j) 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 the AD specifies otherwise. 

(i) Eurocopter Alert Service Bulletin No. 

AS350–05.00.64, Revision 0, dated August 

30, 2011. 

(ii) Eurocopter Alert Service Bulletin No. 

AS355–05.00.59, Revision 0, dated August 

30, 2011. 

(3) For Eurocopter service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax (972) 

641–3775; or at http://www.eurocopter.com/ 

techpub. 

(4) You may view this service information 

that is incorporated by reference in the AD 

Docket on the Internet at http://

www.regulations.gov. 

(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://


sroberts on DSK5SPTVN1PROD with RULES
Federal Register / Vol. 78, No. 171 / Wednesday, September 4, 2013 / Rules and Regulations 54383 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on August 12, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–20238 Filed 9–3–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0239; Directorate 

Identifier 2010–SW–087–AD; Amendment 

39–17552; AD 2013–16–14] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Eurocopter Deutschland GmbH (ECD) 

EC 135 P1, P2, P2+, T1, T2, and T2+ 

helicopters equipped with a certain 

main transmission housing upper part. 

This AD requires installing a corrugated 

washer in the middle of the main 

transmission filter housing upper part 

and modifying the main transmission 

housing upper part. This AD was 

prompted by an inspection of housing 

upper parts that revealed the bypass 

inlet in the oil filter area was not 

manufactured in accordance with 

applicable design specifications. The 

actions of this AD are intended to 

prevent failure of the main transmission 

and subsequent loss of control of the 

helicopter. 

DATES: This AD is effective October 9, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of October 9, 2013. 

ADDRESSES: For service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052, 

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

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

www.eurocopter.com/techpub. You may 

review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov 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 AD, the foreign 

authority’s AD, any incorporated-byreference service information, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (phone: 800–647–5527) is U.S. 

Department of Transportation, Docket 

Operations Office, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Chinh Vuong, Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; telephone 

(817) 222–5110; email chinh.vuong@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On March 14, 2013, at 78 FR 16196, 

the Federal Register published our 

notice of proposed rulemaking (NPRM), 

which proposed to amend 14 CFR part 

39 to include an AD that would apply 

to ECD Model EC135 P1, P2, P2+, T1, 

T2, and T2+ helicopters with a certain 

serial numbered main transmission 

FS108 housing upper part, part number 

(P/N) 4649 301 034. The NPRM 

proposed to require installing a 

corrugated washer in the filter housing 

of the housing upper part and modifying 

each affected main transmission 

housing upper part by machining the oil 

filter bypass inlet. The proposed 

requirements were intended to prevent 

failure of the main transmission and 

subsequent loss of control of the 

helicopter. 

The NPRM was prompted by AD No. 

2010–0213, dated October 14, 2010, 

issued by the European Aviation Safety 

Agency (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 the ECD model EC 135 and 

EC635 helicopters. EASA advises that a 

recent inspection on some housing 

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 

advises 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 requires a 

temporary modification of the main 

transmission housing 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (78 FR 16196 March 14, 2013). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of the Republic 

of Germany and are approved for 

operation in the United States. Pursuant 

to our bilateral agreement with the 

Republic of Germany, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Related Service Information 

ECD has issued Alert Service Bulletin 

(ASB) ASB EC135–63A–017, Revision 0, 

dated October 11, 2010 (EC135–63A– 

017), which specifies removing the oil 

filter element and installing a 

corrugated washer. EC135–63A–017 

also specifies reworking the affected 

filter housing upper part at the next 

repair or major overhaul of the main 

transmission, no later than 4,000 flight 

hours after receipt of the service 

bulletin. EASA classified this ASB as 

mandatory and issued AD 2010–0213 to 

ensure the continued airworthiness of 

these helicopters. 

We have 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 housing upper part. 

Costs of Compliance 

We estimate that this AD will affect 

227 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 AD. Installing the 

corrugated washer will require about .5 

work hour, and required parts cost 

about $10, for a cost per helicopter of 

about $53, and a total cost to the U.S. 


sroberts on DSK5SPTVN1PROD with RULES