This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents.

Rules and Regulations Federal Register

38951 

Vol. 83, No. 153 

Wednesday, August 8, 2018 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0889; Product 

Identifier 2009–NE–35–AD; Amendment 39– 

19305; AD 2018–12–01] 

RIN 2120–AA64 

Airworthiness Directives; Safran 

Helicopter Engines, S.A., Turboshaft 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2012–03– 

11 for all Safran Helicopter Engines, 

S.A., Arriel 2B and 2B1 turboshaft 

engines. AD 2012–03–11 required 

checking the transmissible torque 

between the low-pressure (LP) pump 

impeller and the high-pressure (HP) 

pump shaft on the HP/LP pump and 

metering valve assembly, hereafter 

referred to as the hydro-mechanical 

metering unit (HMU). Since we issued 

AD 2012–03–11, the manufacturer 

determined that incorporating 

Modification TU 178 is a more effective 

method to reduce the risk of uncoupling 

between the LP fuel pump impeller and 

the HP fuel pump shaft than the prior 

Modification TU 147. This AD requires 

inspection and possible replacement of 

the HMU. This AD was prompted by 

three cases of uncoupling of the HMU 

LP fuel pump impeller and the HP fuel 

pump shaft since AD 2012–03–11 was 

issued. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective September 

12, 2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 11, 2010 (75 FR 5689, 

February 4, 2010). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 20, 2012 (77 FR 8092, 

February 14, 2012). 

ADDRESSES: For service information 

identified in this final rule, contact 

Safran Helicopter Engines, S.A., 40220 

Tarnos, France; phone: (33) 05 59 74 40 

00; fax: (33) 05 59 74 45 15. You may 

view this service information at the 

FAA, Engine and Propeller Standards 

Branch, 1200 District Avenue, 

Burlington, MA 01803. For information 

on the availability of this material at the 

FAA, call 781–238–7759. It is also 

available on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2009– 

0889. 

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–2009– 

0889; or in person at Docket Operations 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this final rule, 

the mandatory continuing airworthiness 

information, regulatory evaluation, any 

comments received, and other 

information. The address for Docket 

Operations (phone: 800–647–5527) is 

Document Operations, 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: John 

Frost, Aerospace Engineer, ECO Branch, 

FAA, 1200 District Avenue, Burlington, 

MA 01803; phone: 781–238–7756; fax: 

781–238–7199; email: john.frost@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2012–03–11, 

Amendment 39–16953 (77 FR 8092, 

February 14, 2012), (‘‘AD 2012–03–11’’). 

AD 2012–03–11 applied to all Safran 

Helicopter Engines, S.A., Arriel 2B and 

2B1 turboshaft engines. The NPRM 

published in the Federal Register on 

October 6, 2017 (82 FR 46727). The 

NPRM was prompted by instances of 

uncoupling between the LP fuel pump 

impeller and the HP fuel pump shaft. 

The NPRM proposed to require 

inspection and, depending on the 

results of the inspection, possible 

replacement of the HMU. The NPRM 

also proposed to require replacement of 

pre-Modification TU 178 HMUs with an 

HMU incorporating Modification TU 

178 within 2,200 engine flight hours or 

72 months, whichever occurs first, after 

the effective date of this AD. We are 

issuing this AD to address the unsafe 

condition on these products. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to the comment. 

Request To Clarify Reason for AD 

An individual commenter questioned 

how the new modification in this AD is 

better and different from the actions 

required by the previous AD 2012–03– 

11. 

AD 2012–03–11 required a check of 

the transmissible torque between the LP 

fuel pump impeller and the HP fuel 

pump shaft and replacement of the 

HMU if it does not pass the torque 

check. Since we issued AD 2012–03–11, 

Safran Service Bulletin (SB) 292 73 

2178, Version A, dated April 1, 2015 

introduced Modification TU 178. This 

AD accepts Modification TU 178 as a 

more robust drive link between the LP 

fuel pump impeller and the HP fuel 

pump shaft that ensures the LP impeller 

pump is driven even if the link with the 

drive shaft loosens. This AD requires 

installation of a Modification TU 178 

HMU for any HMU that fails the torque 

sensor check and as a mandatory 

terminating action for the inspections 

required by this AD, as well as purging 

the fleet of the pre- and post-TU 147 

configuration parts. We did not change 

this AD. 

Clarification to Service Information for 

Torque Check 

We updated paragraphs (g)(1)(i) and 

(ii) of this AD to clarify that only 

paragraph 2.A, rather than paragraph 2, 

in Turbomeca Alert Mandatory SB 

(MSB) A292 73 2830, Version B, dated 

July 10, 2009, and Turbomeca Alert 

MSB A292 73 2836, Version A, dated 

August 17, 2010, is used to perform the 

torque check. 


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38952 Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Rules and Regulations 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

addressing the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Turbomeca, S.A., Alert 

MSB A292 73 2830, Version B, dated 

July 10, 2009, and Alert MSB A292 73 

2836, Version A, dated August 17, 2010. 

Turbomeca Alert MSB A292 73 2830, 

Version B, describes procedures for 

inspecting pre-Modification TU 147 

HMUs. Turbomeca Alert MSB A292 73 

2836, Version A, dated August 17, 2010, 

describes procedures for inspecting 

HMUs that have incorporated 

Modification TU 147. 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 Safran Helicopter 

Engines MSB 292 73 2178, Version B, 

dated March 23, 2017. Safran Helicopter 

Engines MSB 292 73 2178, Version B, 

describes HMU improvements that 

includes a reinforced drive link between 

the LP impeller and HP fuel pump shaft 

(Modification TU 178). Safran 

Helicopter Engines has also issued MSB 

A292 73 2830, Version C; and A292 73 

2836, Version B, both dated April 5, 

2017, which exempt HMUs 

incorporating Modification TU 178 from 

the inspections previously 

recommended by Safran Helicopter 

Engines. 

Costs of Compliance 

We estimate that this AD affects 417 

engines installed on helicopters of U.S. 

registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Remove and replace the HP/LP fuel pump 

metering unit.

2 work-hours × $85 per hour = $170 ............. $17,400 $17,570 $7,326,690 

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 engines, propellers, and 

associated appliances to the Manager, 

Engine and Propeller Standards Branch, 

Policy and Innovation Division. 

Regulatory Findings 

We have 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) 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, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2012–03–11, Amendment 39–16953 (77 

FR 8092, February 14, 2012), and adding 

the following new AD: 

2018–12–01 Safran Helicopter Engines 

(Type Certificate previously held by 

Turbomeca, S.A.): Amendment 39– 

19305; Docket No. FAA–2009–0889; 

Product Identifier 2009–NE–35–AD. 

(a) Effective Date 

This AD is effective September 12, 2018. 

(b) Affected ADs 

This AD replaces AD 2012–03–11, 

Amendment 39–16953 (77 FR 8092, February 

14, 2012). 

(c) Applicability 

This AD applies to Safran Helicopter 

Engines, S.A., Arriel 2B and 2B1 turboshaft 

engines, except those incorporating 

Modification TU 178. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7300, Engine Fuel and Control. 

(e) Unsafe Condition 

This AD was prompted by analysis that 

indicated the modification of an engine to 

incorporate Modification TU 178 provides a 

more effective method than Modification TU 


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Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Rules and Regulations 38953 

147 to reduce the risk of uncoupling between 

the low-pressure (LP) fuel pump impeller 

and the high-pressure (HP) fuel pump shaft 

of the HP/LP pump and hydro-mechanical 

metering unit (HMU). We are issuing this AD 

to prevent failure of the HMU. The unsafe 

condition, if not corrected, could result in 

failure of the engine, in-flight shutdown, and 

loss of the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Check the transmissible torque between 

the LP fuel pump impeller and the HP fuel 

pump shaft as follows: 

(i) For pre-Modification TU 147 HMUs, 

check the torque before accumulating 500 

engine flight hours (FHs) since March 11, 

2010 or before the next flight after the 

effective date of this AD, whichever occurs 

later. Use Paragraph 2.A. of Turbomeca Alert 

Mandatory Service Bulletin (MSB) A292 73 

2830, Version B, dated July 10, 2009 to do 

the check. 

(ii) For HMUs that incorporated 

Modification TU 147 on or before March 31, 

2010, and those HMUs not listed in Figure 

2 or 3 of Turbomeca Alert MSB A292 73 

2836, Version A, dated August 17, 2010, 

check the torque before the next flight after 

the effective date of this AD. Use Paragraph 

2.A. of Turbomeca Alert MSB A292 73 2836, 

Version A, dated August 17, 2010, to do the 

check. 

(2) If the HMU does not pass the torque 

check, replace the HMU with a postModification TU 178 HMU before the next 

flight after the effective date of this AD. 

(h) Mandatory Terminating Action 

Within 2,200 engine FHs or 72 months 

after the effective date of this AD, whichever 

occurs first, replace any pre-Modification TU 

178 HMU with a post-Modification TU 178 

configuration HMU. 

(i) Installation Prohibition 

After the effective date of this AD, do not 

install a pre-Modification TU 178 HMU on 

engines incorporating a post-Modification TU 

178 HMU. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO 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 manager of the certification office, 

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 John Frost, Aerospace Engineer, ECO 

Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7756; fax: 781–238–7199; email: john.frost@

faa.gov. 

(2) Refer to European Aviation Safety 

Agency (EASA) AD 2017–0102, dated June 

13, 2017, for more information. You may 

examine the EASA AD on the internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2009–0889. 

(l) 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. 

(3) The following service information was 

approved for IBR on March 11, 2010 (75 FR 

5689, February 4, 2010). 

(i) Turbomeca Alert Mandatory Service 

Bulletin (MSB) No. A292 73 2830, Version B, 

dated July 10, 2009. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on March 20, 2012 (77 FR 

8092, February 14, 2012). 

(i) Turbomeca Alert MSB No. A292 73 

2836, Version A, dated August 17, 2010. 

(ii) Reserved. 

(5) For Safran Helicopter Engines, S.A, 

service information identified in this AD, 

contact Safran Helicopter Engines, S.A., 

40220 Tarnos, France; phone: (33) 05 59 74 

40 00; fax: (33) 05 59 74 45 15. 

(6) You may view this service information 

at FAA, Engine and Propeller Standards 

Branch, 1200 District Avenue, Burlington, 

MA 01803. For information on the 

availability of this material at the FAA, call 

781–238–7759. 

(7) 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 Burlington, Massachusetts, on 

July 31, 2018. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2018–16652 Filed 8–7–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0640; Product 

Identifier 2018–NM–075–AD; Amendment 

39–19343; AD 2018–16–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus SAS Model A319–133 airplanes 

and Model A321–232 airplanes. This 

AD requires modification and reidentification, or replacement, of certain 

engine fan cowl doors (FCDs) and 

installation of a placard in the flight 

deck. This AD was prompted by reports 

of in-service engine FCD losses, and the 

development of a new FCD front latch 

and keeper assembly that addresses this 

unsafe condition. We are issuing this 

AD to address the unsafe condition on 

these products. 

DATES: This AD becomes effective 

August 23, 2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 3, 2017 (82 FR 29371, June 

29, 2017). 

We must receive comments on this 

AD by September 24, 2018. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this final rule, contact Airbus SAS, 

Airworthiness Office—EIAS, RondPoint Emile Dewoitine No: 2, 31700 

Blagnac Cedex, France; telephone +33 5 

61 93 36 96; fax +33 5 61 93 44 51; email 


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