Federal Register / Vol. 85, No. 244 / Friday, December 18, 2020 / Rules and Regulations 82305 

the (Rolls-Royce) RR Trent-768–60/15 Engine 

Manual. 

(3) For service information identified in 

this AD, contact Rolls-Royce plc, P.O. Box 

31, Derby, DE24 8BJ, United Kingdom, 

phone: +44 (0)1332 242424; website: https:// 

www.rolls-royce.com/contact-us.aspx. 

(4) You may view this service information 

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 1200 District 

Avenue, Burlington, MA 01803. For 

information on the availability of this 

material at the FAA, call (781) 238–7759. 

(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, 

email: fedreg.legal@nara.gov, or go to: 

https://www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

Issued on November 17, 2020. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2020–27897 Filed 12–17–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0572; Product 

Identifier 2017–SW–056–AD; Amendment 

39–21358; AD 2020–26–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2007–26– 

51 which applied to certain Airbus 

Helicopters Deutschland GmbH Model 

EC135 helicopters. AD 2007–26–51 

required inspecting the tail rotor control 

rod (control rod) and ball pivot and, 

depending on findings, replacing those 

parts. This new AD requires inspecting 

certain ball pivots, applying corrosion 

preventative compound on the ball 

pivot, and corrective action, as 

applicable. This AD also requires 

replacing the control rod with a newly 

developed control rod. This AD was 

prompted by the manufacturer’s 

development of a new control rod, 

which the FAA has determined must be 

installed in order to address the 

identified unsafe condition. The actions 

of this AD are intended to address an 

unsafe condition on these products. 

DATES: This AD is effective January 22, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 22, 2021. 

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 https://

www.airbus.com/helicopters/services/ 

technical-support.html. You may view 

this 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 https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0572. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://

www.regulations.gov in Docket No. 

FAA–2020–0572; 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 (now European Union Aviation 

Safety Agency) (EASA) AD, any service 

information that is incorporated by 

reference, any comments received, and 

other information. The street address for 

Docket Operations 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: 

David Hatfield, Aviation Safety 

Engineer, Aircraft Systems Section, 

Technical Innovation Policy Branch, 

FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone 817–222– 

5116; email David.Hatfield@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to remove AD 2007–26–51, 

Amendment 39–15357 (73 FR 6008, 

February 1, 2008) (AD 2007–26–51), and 

add a new AD. AD 2007–26–51 applied 

to certain Airbus Helicopters 

Deutschland GmbH (type certificate 

previously held by Eurocopter 

Deutschland GmbH) Model EC135 

helicopters, serial number (S/N) 0005 

up to and including S/N 0444, except S/ 

N 0028, and with control rod part 

number (P/N) L672M2005207, installed. 

The NPRM was published in the 

Federal Register on June 18, 2020 (85 

FR 36816). The NPRM proposed to 

require inspecting certain ball pivots for 

damage and freedom of movement, 

applying corrosion preventative 

compound on the ball pivot, and 

corrective action, as applicable. The 

NPRM also proposed to require 

replacing the control rod with the newly 

developed control rod that the FAA 

determined was necessary to address 

the unsafe condition. 

The NPRM was prompted by EASA 

AD No. 2010–0227R1, dated April 7, 

2017 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), issued by 

EASA, which is the Technical Agent for 

the Member States of the European 

Union, to correct an unsafe condition 

for all Model EC135 P1, EC135 P2, 

EC135 P2+, EC135 T1, EC 135 T2, and 

EC135 T2+ helicopters; and Model 

EC635 T1, EC635 P2+, and EC635 T2+ 

helicopters. EASA advises that in 2007 

an accident occurred on an EC135 

helicopter in Japan. Preliminary 

investigation results indicated that loss 

of control was due to failure of the 

control rod. EASA issued EASA 

Emergency AD 2007–0301–E, dated 

December 13, 2007 (EASA AD 2007– 

0301–E) to inspect the affected control 

rod P/N L672M2005207 and the ball 

pivot (which correspond to the actions 

required by AD 2007–26–51). EASA AD 

2007–0301–E was subsequently 

superseded by EASA AD 2007–0313, 

dated December 21, 2007, to require 

repetitive inspections and, depending 

on findings, the replacement of the 

control rod and ball pivot, only for 

helicopters not equipped with an 

automatic flight control system (AFCS). 

After review of the inspection results, 

EASA issued EASA AD 2008–0064, 

dated April 4, 2008, and later revised to 

EASA AD 2008–0064 R1, dated April 

15, 2008 (EASA AD 2008–0064 R1), to 

apply the requirements to helicopters 

equipped with an AFCS. 

EASA also advises that after EASA 

AD 2008–0064R1 was issued, 

Eurocopter Deutschland GmbH 

developed a new control rod P/N 

L672M2006101, installation of which 

constituted terminating action for the 

repetitive inspections. Consequently, 

EASA issued EASA AD 2010–0227, 

dated November 3, 2010, and corrected 

November 8, 2010, retaining the 

requirements of EASA AD 2008– 

0064R1, and requiring the replacement 

of control rod P/N L672M2005207 with 

the new control rod P/N 

L672M2006101. The FAA has 

determined that this new control rod 

must be installed in order to address the 

unsafe condition. 

In addition, EASA advises that 

following a review of data and feedback 

received from in-service helicopters, it 


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82306 Federal Register / Vol. 85, No. 244 / Friday, December 18, 2020 / Rules and Regulations 

has been determined that the repetitive 

inspections of the ball pivot are no 

longer required to address the unsafe 

condition. The repetitive inspections of 

the ball pivot are now included in 

Chapter 05 of the aircraft maintenance 

manual. Therefore, EASA issued EASA 

AD 2010–0227R1 to remove the 

requirement for repetitive inspections of 

the control rod and of the ball pivot. 

You may examine the MCAI in the 

AD docket on the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0572. 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule, but the FAA did not 

receive any comments on the NPRM or 

on the determination of the cost to the 

public. 

FAA’s Determination 

These helicopters have been approved 

by EASA and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with the 

European Union, EASA has notified the 

FAA of the unsafe condition described 

in its AD. The FAA is issuing this AD 

after evaluating all of the information 

provided by EASA and determining the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

the same type designs and that air safety 

and the public interest require adopting 

the AD requirements as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

The MCAI includes a compliance 

time of 50 flight hours for the inspection 

of a certain ball pivot; 100 flight hours 

or 43 days for the inspection of a certain 

other ball pivot; and 400 flight hours or 

12 months for the replacement of the 

control rod. This AD requires all actions 

be accomplished within 50 hours timein-service. 

The MCAI applies to Airbus 

Helicopters Deutschland GmbH Model 

EC635 T1, EC635 P2+, and EC635 T2+ 

helicopters. Model EC635 T1, EC635 

P2+, and EC635 T2+ helicopters are not 

certified by the FAA and are not 

included on the U.S. type certificate 

data sheet except where the U.S. type 

certificate data sheet explains that the 

Model EC635T2+ helicopter having 

serial number 0858 was converted from 

Model EC635T2+ to Model EC135T2+; 

this AD therefore does not include those 

Model EC 635 helicopters in the 

applicability. 

Additionally, although the MCAI and 

service information specify to contact 

the manufacturer, this AD does not 

include that requirement. 

Related Service Information Under 1 

CFR Part 51 

Airbus Helicopters has issued Alert 

Service Bulletin ASB EC135–67A–017, 

Revision 4, dated April 3, 2017, 

including the Appendix (watermarked 

as Appendix to SB EC135–67A–017 

Revision 4). This service information 

describes procedures for, among other 

actions, an inspection of ball pivots, P/ 

Ns 92–201–00 and 92–207–00, for 

freedom of movement, and for damage 

(e.g., cracks, missing hardware, loose 

bearing, or play), application of 

corrosion preventative compound, and 

corrective actions. Corrective actions 

include replacing the ball pivot and the 

control rod with serviceable parts, and 

applying corrosion preventative 

compound. 

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 

Eurocopter has issued Service 

Bulletin EC135–67–018, Revision 01, 

dated May 15, 2008, which describes 

procedures for replacing the control rod 

having P/N L672M2005207 with a 

control rod having P/N L672M2006101. 

Eurocopter has also issued Alert 

Service Bulletin EC135–67A–017, 

Revision 03, dated July 26, 2010, which 

describes procedures for ball pivot 

inspections and replacements. 

Costs of Compliance 

The FAA estimates that this AD 

affects 311 helicopters of U.S. Registry. 

The FAA estimates that operators may 

incur the following costs in order to 

comply with this AD. Labor costs are 

estimated at $85 per work-hour. 

Inspecting the ball pivot takes about 

1 work-hour, for an estimated cost of 

$85 per helicopter and $26,435 for the 

U.S. fleet. If applicable, applying 

corrosion preventative compound takes 

a minimal amount of additional time for 

a nominal cost. 

Replacing the control rod takes about 

3 work-hours, and parts cost about $800 

for an estimated cost of $1,055 per 

helicopter and $328,105 for the U.S. 

fleet. 

Replacing the control rod and ball 

pivot takes up to about 6 work-hours, 

and parts cost up to about $2,150 for an 

estimated cost of up to $2,660 per 

helicopter. 

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. 

The FAA is 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 

The FAA has determined that 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) Will not affect intrastate aviation 

in Alaska, and 

(3) 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: 

■ a. Removing Airworthiness Directive 

(AD) 2007–26–51, Amendment 39– 


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Federal Register / Vol. 85, No. 244 / Friday, December 18, 2020 / Rules and Regulations 82307 

15357 (73 FR 6008, February 1, 2008), 

and 

■ b. Adding the following new AD: 

2020–26–03 Airbus Helicopters 

Deutschland GmbH: Amendment 39– 

21358; Docket No. FAA–2020–0572; 

Product Identifier 2017–SW–056–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective January 22, 2021. 

(b) Affected ADs 

This AD replaces AD 2007–26–51, 

Amendment 39–15357 (73 FR 6008, February 

1, 2008) (AD 2007–26–51). 

(c) Applicability 

This AD applies to Airbus Helicopters 

Deutschland GmbH Model EC135P1, 

EC135T1, EC135P2, EC135T2, EC135P2+, 

EC135T2+, EC135P3, and EC135T3 

helicopters, certificated in any category, all 

serial numbers. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6700, Rotorcraft Flight Control. 

(e) Reason 

This AD was prompted by an accident 

involving the failure of a tail rotor control 

rod. The FAA is issuing this AD to address 

failure of a tail rotor control rod and 

subsequent loss of control of the helicopter. 

(f) 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. 

(g) Definitions 

(1) Group 1: Helicopters that, on the 

effective date of this AD, have a tail rotor 

control rod installed having part number (P/ 

N) L672M2005207. 

(2) Group 2: Helicopters that, on the 

effective date of this AD, do not have a tail 

rotor control rod installed having P/N 

L672M2005207. 

(h) Ball Pivot Inspection 

Within 50 hours time-in-service after the 

effective date of this AD: Inspect the ball 

pivot, P/N 92–201–00 and P/N 92–207–00, 

for damage and freedom of movement, in 

accordance with step 3.C.(3) or step 3.D.(3), 

as applicable, of the Accomplishment 

Instructions of the Appendix (watermarked 

as Appendix to SB EC135–67A–017 Revision 

4) to Airbus Helicopters Alert Service 

Bulletin ASB EC135–67A–017, Revision 4, 

dated April 3, 2017. For purposes of this 

inspection, damage to the ball pivot may be 

indicated by cracks, missing hardware, loose 

bearings, or play. 

(i) Corrective Action 

If, during the inspection required by 

paragraph (h) of this AD, there is any damage 

on any ball pivot or the ball pivot cannot be 

moved: Before further flight, replace the ball 

pivot in accordance with step 3.C.(3) or step 

3.D.(3), as applicable, of the Accomplishment 

Instructions of the Appendix (watermarked 

as Appendix to SB EC135–67A–017 Revision 

4) to Airbus Helicopters Alert Service 

Bulletin ASB EC135–67A–017, Revision 4, 

dated April 3, 2017, and the tail rotor control 

rod as required by paragraph (j) of this AD. 

(j) Tail Rotor Control Rod Replacement 

Group 1: Unless already done as required 

by paragraph (i) of this AD, within 50 hours 

time-in-service after the effective date of this 

AD, replace the tail rotor control rod having 

P/N L672M2005207 with a tail rotor control 

rod having P/N L672M2006101. 

Note 1 to paragraph (j): Guidance for 

replacing the tail rotor control rod can be 

found in Eurocopter Service Bulletin EC135– 

67–018, Revision 01, dated May 15, 2008. 

(k) Parts Installation Prohibition 

(1) Group 1: After modification of a 

helicopter as required by paragraphs (i) or (j) 

of this AD, no person may install on any 

helicopter a tail rotor control rod having P/ 

N L672M2005207. 

(2) Group 2: As of the effective date of this 

AD, no person may install on any helicopter 

a tail rotor control rod having P/N 

L672M2005207. 

(l) Credit for Previous Actions 

This paragraph provides credit for the 

inspection and ball pivot replacements 

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

if those actions were performed before the 

effective date of this AD using Eurocopter 

Alert Service Bulletin EC135–67A–017, 

Revision 03, dated July 26, 2010. 

(m) Special Flight Permit 

Special flight permits, as described in 14 

CFR 21.197 and 21.199, are not allowed. 

(n) No Reporting Requirement 

Although the Appendix (watermarked as 

Appendix to SB EC135–67A–017 Revision 4) 

to Airbus Helicopters Alert Service Bulletin 

ASB EC135–67A–017, Revision 4, dated 

April 3, 2017, specifies to contact the 

manufacturer, this AD does not include that 

requirement. 

(o) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Strategic Policy 

Rotorcraft, FAA, may approve AMOCs for 

this AD. Send your proposal to: David 

Hatfield, Aviation Safety Engineer, Aircraft 

Systems Section, Technical Innovation 

Policy Branch, FAA, 10101 Hillwood Pkwy., 

Fort Worth, TX 76177; telephone 817–222– 

5116; 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, the FAA suggests 

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. 

(p) Related Information 

(1) The subject of this AD is addressed in 

European Aviation Safety Agency (now 

European Union Aviation Safety Agency) 

(EASA) AD No. 2010–0227R1, dated April 7, 

2017. This EASA AD may be found in the AD 

docket on the internet at https://

www.regulations.gov by searching for and 

locating Docket No. FAA–2020–0572. 

(2) 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 https://

www.airbus.com/helicopters/services/ 

technical-support.html. You may view 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. 

(q) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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 Helicopters Alert Service 

Bulletin ASB EC135–67A–017, Revision 4, 

dated April 3, 2017. 

(ii) [Reserved] 

(3) 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 https://

www.airbus.com/helicopters/services/ 

technical-support.html. 

(4) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call 817–222–5110. 

(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, 

email fedreg.legal@nara.gov, or go to: https:// 

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

Issued on December 8, 2020. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2020–27808 Filed 12–17–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0574; Product 

Identifier 2019–CE–015–AD; Amendment 

39–21340; AD 2020–24–10] 

RIN 2120–AA64 

Airworthiness Directives; Aerostar 

Aircraft Corporation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 


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