34286 Federal Register / Vol. 78, No. 110 / Friday, June 7, 2013 / Proposed Rules 

(b) Affected ADs 

This AD supersedes AD 2013–01–07, 

Amendment 39–17321 (78 FR 6725, January 

31, 2013). 

(c) Applicability 

This AD applies to all Turbomeca S.A. 

Arriel 2D turboshaft engines. 

(d) Unsafe Condition 

This AD was prompted by further cases of 

deterioration of hydromechanical metering 

unit (HMU) rotating components that have 

been reported before the HMU reached the 

replacement interval in AD 2013–01–07 (78 

FR 6725, January 31, 2013). We are issuing 

this AD to prevent an uncommanded in-flight 

shutdown of the engine, and possible loss of 

the helicopter. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Replace inter-pump complete sleeve, 

and inspect the female splines and HMU 

high-pressure (HP) pump and low-pressure 

(LP) pump male splines for corrosion, 

scaling, cracks and wear, at the following: 

(i) Before exceeding 400 HMU operating 

hours since new if the HMU has 375 or fewer 

operating hours on the effective date of this 

AD; or 

(ii) Within 25 HMU operating hours if the 

HMU has more than 375 operating hours on 

the effective date of this AD; and 

(iii) Thereafter, at intervals not to exceed 

400 HMU operating hours. 

(iv) Use Section 2.B.(1) of the Instructions 

to be Incorporated of Turbomeca S.A. Alert 

Mandatory Service Bulletin (MSB) No. A292 

73 2847, Version B, dated March 6, 2013, to 

accomplish the replacement and visual 

inspection required by paragraph (e)(1) of 

this AD. 

(v) If the HMU does not pass the initial or 

repetitive visual inspections required by 

paragraph (e)(1) of this AD, then before next 

flight, replace the affected HMU with an 

HMU eligible for installation. 

(2) Replace the rotating components of the 

HP and LP pumps, including the complete 

sleeve, or replace the HMU with an HMU 

eligible for installation at the following: 

(i) Before exceeding 800 HMU operating 

hours since new; or 

(ii) Within 800 HMU operating hours since 

last replacement of LP and HP fuel pumps 

rotating components; whichever occurs later. 

(iii) Thereafter, replace the LP and HP fuel 

pump rotating components within every 800 

HMU operating hours. 

(iv) Use Section 2.B.(1) of the Instructions 

to be Incorporated of Turbomeca S.A. Alert 

MSB No. A292 73 2847, Version B, dated 

March 6, 2013, to accomplish the 

replacements required by paragraph (e)(2) of 

this AD. 

(f) Credit for Previous Actions 

If before the effective date of this AD, you 

complied with Turbomeca S.A. Alert MSB 

No. A292 73 2847, Version A, dated May 29, 

2012, you met the initial inspection 

requirements in paragraph (e) of this AD. 

However, you must still comply with the 

repetitive inspection requirements of this 

AD. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

install any HMU onto any engine, or install 

any engine onto any helicopter, unless the 

HMU is in compliance with this AD. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7779; fax: 781–238–7199; 

email: frederick.zink@faa.gov. 

(2) European Aviation Safety Agency AD 

2013–0079, dated March 22, 2013, 

Turbomeca S.A. Alert MSB No. A292 73 

2847, Version B, dated March 6, 2013, and 

Turbomeca Maintenance Manual Task 73– 

23–00–802–A01, pertain to the subject of this 

AD. 

(3) For service information identified in 

this AD, contact Turbomeca, 40220 Tarnos, 

France; phone: 33 (0)5 59 74 40 00; telex: 570 

042; fax: 33 (0)5 59 74 45 15. You may view 

this service information at the FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

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

Issued in Burlington, Massachusetts, on 

June 3, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–13509 Filed 6–6–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0490; Directorate 

Identifier 2008–SW–004–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

(Bell) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Bell Model 407 helicopters. This 

proposed AD would require installing a 

placard beneath the NR/NP dual 

tachometer and revising the limitations 

section of the rotorcraft flight manual 

(RFM). This proposed AD is prompted 

by several incidents of third stage 

engine turbine wheel failures, which 

were caused by excessive vibrations at 

certain engine speeds during steadystate operations. The proposed actions 

are intended to alert pilots to avoid 

certain engine speeds during steadystate operations, prevent failure of the 

third stage engine turbine, engine power 

loss, and subsequent loss of control of 

the helicopter. 

DATES: We must receive comments on 

this proposed AD by August 6, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

For service information identified in 

this proposed AD, contact Bell 

Helicopter Textron Canada Limited, 

12,800 Rue de l’Avenir, Mirabel, Quebec 

J7J1R4; telephone (450) 437–2862 or 

(800) 363–8023; fax (450) 433–0272; or 

at http://www.bellcustomer.com/files/. 

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. 

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. 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
Federal Register / Vol. 78, No. 110 / Friday, June 7, 2013 / Proposed Rules 34287 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

Transport Canada (TC), which is the 

aviation authority for Canada, has 

issued TC AD No. CF–2004–09R1, dated 

July 4, 2005, to correct an unsafe 

condition for Model 407 helicopters. TC 

advises of several failures of third stage 

turbine wheels used in Rolls Royce 250– 

C30S and 250–C47B engines, and three 

of these failures have occurred to the 

250–C47B engine used by Bell on the 

Model 407. According to TC, Rolls 

Royce has determined that detrimental 

vibrations can occur within a particular 

range of turbine speeds, and may be a 

contributing factor to these failures. Bell 

has revised the operating limitations of 

the RFM and provided a corresponding 

decal on the instrument panel to inform 

pilots to avoid steady-state operations 

between 68.4% and 87.1% turbine 

speeds. 

The TC AD requires amending the 

RFMs, advising pilots of the change, and 

installing a decal as described in Bell 

Alert Service Bulletin (ASB) No. 407– 

05–67, dated June 8, 2005 (ASB 407–05– 

67). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Canada and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Canada, TC, its 

technical representative, has notified us 

of the unsafe condition described in its 

AD. We are proposing this AD because 

we evaluated all known relevant 

information and determined that an 

unsafe condition is likely to exist or 

develop on other helicopters of the same 

type design. 

Related Service Information 

Bell has issued ASB 407–05–67, 

which contains procedures for installing 

a placard on the instrument panel below 

the main rotor RPM (Nr)/power turbine 

RPM (Np) dual tachometer and for 

inserting the RFM changes into the 

flight manual. 

Proposed AD Requirements 

This proposed AD would require 

installing a placard on the instrument 

panel below the NR/NP dual tachometer 

and revising the Operating Limitations 

section of the Model 407 RFM to limit 

steady-state operations between speeds 

of 68.4% to 87.1%. 

Differences Between This Proposed AD 

and the TC AD 

The TC AD requires compliance 

within 10 calendar days; the proposed 

AD requires compliance within 30 days. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 472 helicopters of U.S. 

Registry. Based on an average labor rate 

of $85 per hour, we estimate that 

operators may incur the following costs 

in order to comply with this AD. 

Amending the RFM would require about 

0.5 work-hours, for a cost per helicopter 

of about $43 and a cost to U.S. operators 

of $20,296. Installing the decal would 

require about 0.2 work-hours and 

required parts would cost $20, for a cost 

per helicopter of $37 and a cost to U.S. 

operators of $17,464. Based on these 

estimates, the total cost of this proposed 

AD would be $80 per helicopter and 

$37,760 for the U.S. operator fleet. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed, I certify 

this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska to the extent that it justifies 

making a regulatory distinction; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by Reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Bell Helicopter Textron Canada Limited 

(Bell): Docket No. FAA–2013–0490; 

Directorate Identifier 2008–SW–004–AD. 

(a) Applicability 

This AD applies to Bell Model 407 

helicopters, serial numbers 53000 through 

53644, certificated in any category. 


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34288 Federal Register / Vol. 78, No. 110 / Friday, June 7, 2013 / Proposed Rules 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

third stage turbine vibration, which could 

result in turbine failure, engine power loss, 

and subsequent loss of control of the 

helicopter. 

(c) Comments Due Date 

We must receive comments by August 6, 

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 

Within 30 days: 

(1) Revise the Operating Limitations 

section of the Model 407 Rotorcraft Flight 

Manual by inserting Section 1, Operating 

Limitations, pages 1–6 and 1–14, of Bell 

BHT–407–FM–1, revision 3, dated April 26, 

2005. 

(2) Remove placard part number (P/N) 

230–075–213–105, if installed. 

(3) Install placard P/N 230–075–213–111, 

or equivalent, directly below the NR/NP dual 

tachometer. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: 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. 

(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. 

(g) Additional Information 

(1) Bell Alert Service Bulletin No. 407–05– 

67, dated June 8, 2005, which is not 

incorporated by reference, contains 

additional information about the subject of 

this AD. For service information identified in 

this AD, contact Bell Helicopter Textron 

Canada Limited, 12,800 Rue de l’Avenir, 

Mirabel, Quebec J7J1R4; telephone (450) 

437–2862 or (800) 363–8023; fax (450) 433– 

0272; or at http://www.bellcustomer.com/ 

files/. You may review a copy of the service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

Transport Canada AD No. CF–2004–09R1, 

dated July 4, 2005. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7250: Turbine Section. 

Issued in Fort Worth, Texas, on May 29, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–13477 Filed 6–6–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0487; Directorate 

Identifier 2010–SW–056–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for 

Eurocopter France (Eurocopter) Model 

AS332L2 and EC225LP helicopters. This 

proposed AD would require inspecting 

the torque value of the bolts that secure 

the front and rear main gearbox (MGB) 

suspension bar attaching fittings, and retorqueing the bolts to the proper value 

if the torque value is out of tolerance. 

This proposed AD would also require, if 

the torque value is out of tolerance by 

more than 20 percent, inspecting the 

bolts, frames, and related equipment for 

a crack and repairing or replacing them 

if cracked. This proposed AD is 

prompted by reports of cracks on Frame 

5295 of Model AS332L2 helicopters. 

These actions are intended to detect the 

torque loss of the bolts that secure the 

MGB bar attaching fittings and to 

prevent cracks that could lead to failure 

of the MGB supporting structure, 

detachment of the MGB, and loss of 

helicopter control. 

DATES: We must receive comments on 

this proposed AD by August 6, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

For service information identified in 

this proposed 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. 

FOR FURTHER INFORMATION CONTACT: Gary 

Roach, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1