Federal Register / Vol. 82, No. 193 / Friday, October 6, 2017 / Proposed Rules 46727 

provisions of paragraphs (i)(4)(i) and (i)(4)(ii) 

of this AD apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. An AMOC is required for any 

deviations to RC steps, including substeps 

and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(j) Related Information 

(1) For more information about this AD, 

contact Lu Lu, Aerospace Engineer, Airframe 

Section, FAA, Seattle ACO Branch, 1601 

Lind Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6478; fax: 425–917–6590; 

email: lu.lu@faa.gov. 

(2) For service information identified in 

this AD, contact Aviation Partners Boeing, 

2811 South 102nd Street, Suite 200, Seattle, 

WA 98168; phone: 1–206–830–7699; fax: 1– 

206–767–3355; email: leng@

aviationpartners.com; Internet: http://

www.aviationpartnersboeing.com. You may 

view this referenced service information at 

the FAA, Transport Standards Branch, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

Issued in Renton, Washington, on 

September 25, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–21225 Filed 10–5–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0889; Product 

Identifier 2009–NE–35–AD] 

RIN 2120–AA64 

Airworthiness Directives; Safran 

Helicopter Engines, S.A., Turboshaft 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2012–03– 

11 that applies to all Safran Helicopter 

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

turboshaft engines. AD 2012–03–11 

requires 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 proposed AD 

would require inspection and possible 

replacement of the HMU. We are 

proposing this AD to address the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by November 20, 

2017. 

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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact 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. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

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 the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

mandatory continuing airworthiness 

information, regulatory evaluation, any 

comments received, and other 

information. The address for the Docket 

Office (phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Robert Green, Aerospace Engineer, ECO 

Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781– 

238–7754; fax: 781–238–7199; email: 

robert.green@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2009–0889; Product Identifier 2009– 

NE–35–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this NPRM. We will consider 

all comments received by the closing 

date and may amend this NPRM 

because of those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this NPRM. 

Discussion 

We issued AD 2012–03–11, 

Amendment 39–16953 (77 FR 8092, 

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

for all Turbomeca S.A. Arriel 2B and 

2B1 turboshaft engines. AD 2012–03–11 

requires checking the transmissible 

torque between the LP pump impeller 

and the HP pump shaft on the pre- and 

post-Modification TU 147 HMUs. AD 

2012–03–11 resulted from instances of 

uncoupling between the LP fuel pump 

impeller and the HP fuel pump shaft. 

We issued AD 2012–03–11 to prevent an 

uncommanded in-flight shutdown, 

which can result in a forced 

autorotation landing or accident. 

Actions Since AD 2012–03–11 Was 

Issued 

Since we issued AD 2012–03–11, the 

manufacturer determined that 

modification of an engine to incorporate 

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. Also since we 

issued AD 2012–03–11, the European 

Aviation Safety Agency (EASA) has 

issued AD 2017–0102, dated June 13, 

2017, which requires inspection and 

possible replacement of the HMU. 


asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
46728 Federal Register / Vol. 82, No. 193 / Friday, October 6, 2017 / Proposed Rules 

Related Service Information Under 1 

CFR Part 51 

Turbomeca, S.A., has issued Alert 

Mandatory Service Bulletin (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, is 

used to do the inspection for preModification TU 147 HMUs. Turbomeca 

Alert MSB A292 73 2836, Version A, is 

used to do the inspection for 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 

Safran Helicopter Engines has issued 

MSB 292 73 2178, Version B, dated 

March 23, 2017, introducing an HMU 

with a reinforced drive link between the 

LP impeller and fuel pump drive 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 Turbomeca. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

inspection and, depending on the 

results of the inspection, possible 

replacement of the HMU. This proposed 

AD would further 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 later, after 

the effective date of this AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 417 engines installed on 

helicopters of U.S. registry. 

We estimate the following costs to 

comply with this proposed 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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would not 

have a substantial direct effect on the 

States, on the relationship between the 

national Government and the States, or 

on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the 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. 

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) 

2012–03–11, Amendment 39–16953 (77 

FR 8092, February 14, 2012), and adding 

the following new AD: 

Safran Helicopter Engines (Type Certificate 

previously held by Turbomeca, S.A.): 

Docket No. FAA–2009–0889; Product 

Identifier 2009–NE–35–AD. 

(a) Comments Due Date 

We must receive comments by November 

20, 2017. 

(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 


asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
Federal Register / Vol. 82, No. 193 / Friday, October 6, 2017 / Proposed Rules 46729 

more effective method than Modification TU 

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. 

(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, whichever 

occurs later. Use Paragraph 2 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 Figures 

2 or 3 of Turbomeca Alert MSB A292 73 

2836, Version A, dated August 17, 2010, 

check the torque before the next flight. Use 

Paragraph 2 of Turbomeca Alert MSB A292 

73 2836, Version A, 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. 

(g) 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. 

(h) 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. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO Branch, FAA, may 

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. 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. 

(j) Related Information 

(1) For more information about this AD, 

contact Robert Green, Aerospace Engineer, 

ECO Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7754; fax: 781–238–7199; email: 

robert.green@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2017–0102, dated June 13, 

2017, for more information. You may 

examine the MCAI in the AD docket on the 

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

searching for and locating it in Docket No. 

FAA–2009–0889. 

(3) For 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. You may 

view this referenced 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 

781–238–7125. 

Issued in Burlington, Massachusetts, on 

September 29, 2017. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2017–21344 Filed 10–5–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0902; Product 

Identifier 2016–NM–188–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2004–03– 

07, which applies to certain Airbus 

Model A320–111, –211, –212, and –231 

series airplanes. AD 2004–03–07 

requires repetitive inspections for 

fatigue cracking around the fasteners 

attaching the pressure panel to the 

flexible bracket at frame (FR) 36, 

adjacent to the longitudinal beams on 

the left and right sides of the airplane; 

and repair as necessary. Since we issued 

AD 2004–03–07, additional cracking has 

been found under the longitudinal 

beams in locations outside of the 

inspection areas required by AD 2004– 

03–07. This proposed AD would retain 

certain requirements of AD 2004–03–07, 

expand the applicability, and require an 

inspection of the fastener holes on the 

pressure panel between FR 35 and FR 

36 under the longitudinal beam and 

modification or repair as applicable. We 

are proposing this AD to address the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by November 20, 

2017. 

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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact 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. You 

may view this referenced service 

information at the FAA, Transport 

Standards Branch, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0902; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227– 

1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2017–0902; Product Identifier 2016– 

NM–188–AD at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 


asabaliauskas on DSKBBXCHB2PROD with PROPOSALS