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 


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Federal Register / Vol. 78, No. 110 / Friday, June 7, 2013 / Proposed Rules 34289 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

Direction Ge ́ne ́rale de l’Aviation 

Civile (DGAC), the aviation authority for 

France, has issued AD No. F–2006–020 

for Model AS 332 L2 helicopters and 

AD No. F–2006–021 for Model EC 225 

LP helicopters, both dated February 1, 

2006, to correct an unsafe condition in 

those model helicopters. The DGAC 

ADs require conducting visual checks 

after the last flight of each day for cracks 

in the outer skin paneling and the butt 

strap of the MGB sliding cowling left 

and right attachment points on Frame 

5295. If a crack is found in the outer 

skin paneling Zone 2, then the DGAC 

ADs require visually inspecting the 

corresponding Zone 2 of Frame 5295 for 

a crack and suspending all flights if a 

crack is found. If no crack is found 

through visual inspections, the DCAG 

ADs provide instructions for further 

inspections and repairs. Issues with the 

outer skin paneling were resolved by the 

time the FAA certificated the EC225 on 

January 30, 2008. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, issued AD No. 2006–102– 

E, which superseded DGAC AD F– 

2006–021, and AD No. 2006–103–E, 

which superseded DGAC AD F–2006– 

020. Both EASA ADs are dated April 25, 

2006. AD Nos. 2006–102–E and 2006– 

103–E retain the requirements of the 

DGAC ADs but expand the area to be 

inspected. 

EASA then issued AD No. 2006–0163, 

dated June 9, 2006, to supplement the 

requirements of AD Nos. 2006–102–E 

and 2006–103–E by mandating that the 

bolts securing the front and rear of the 

MGB bar attaching fittings be inspected 

for tightening torque loss. According to 

EASA, analysis of the tightening torques 

revealed some cases of tightening torque 

loss, which can lead to the formation of 

a crack at the MGB bar attaching fittings. 

EASA subsequently issued AD No. 

2006–0163 R1, dated December 13, 

2007, which revises and replaces AD 

No. 2006–0163, retaining its 

requirements but extending the 

compliance interval for inspecting the 

bolts on Model EC 225 LP helicopters. 

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 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 products of the same 

type design. 

Related Service Information 

We reviewed Eurocopter Alert Service 

Bulletin (ASB) No. 05.00.65, Revision 0, 

dated March 28, 2006, for Model 

AS332L2 helicopters, and ASB No. 

05A002, Revision 1, dated December 6, 

2007, for Model EC225LP helicopters. 

The ASBs specify inspecting the 

tightening torque of the bolts that secure 

the front and rear of the MGB bar 

attaching fittings. If more than a 20 

percent tightening torque load loss is 

discovered, the ASBs require inspecting 

the frames 3855 and 5295 for a crack in 

the area of the MGB bar attaching 

fittings. EASA classified these ASBs as 

mandatory and issued EASA AD No. 

2006–0163 R1, dated December 13, 

2007, to ensure the continued 

airworthiness of these helicopters. 

Proposed AD Requirements 

This proposed AD would require 

repetitively inspecting the tightening 

torque value of the bolts that secure the 

front and rear MGB suspension bar 

attaching fittings. If the torque value is 

out of tolerance 20 percent or less, then 

the proposed AD would require that 

each bolt be re-torqued to the proper 

value. If the torque value is out of 

tolerance more than 20 percent, then 

this proposed AD would require retorqueing each bolt to the proper value 

and inspecting the bolts, frame, and 

related equipment for a crack. If a 

cracked bolt is detected, this AD would 

require replacing all four attaching 

fitting bolts. If a crack in the frame or 

other equipment is detected, this 

proposed AD would require repairing or 

replacing the cracked frame and other 

equipment. 

Differences Between This Proposed AD 

and the EASA AD 

This AD differs from the EASA AD in 

that we use the word ‘‘inspect’’ to 

describe actions required by a mechanic 

versus the word ‘‘check,’’ which is how 

we describe actions allowed by a pilot. 

We also require that if you find a crack 

in a frame or fitting, you repair or 

replace the cracked part instead of 

contacting the manufacturer. Also, we 

have different compliance times for the 

initial inspection for the tightening 

torque of the bolts that secure the MGB 

attaching fitting. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 4 helicopters of U.S. 

Registry and that labor costs would 

average $85 a work-hour. Based on these 

estimates, we would expect the 

following costs: 

• Inspecting the torque of each bolt 

that secures the front and rear MGB 

attaching fitting would require 1 workhour and no parts for a total cost of $85 

per helicopter, and $340 for the U.S. 

fleet. 

• Readjusting the torque would add 

another 0.25 work-hour for a total cost 

of about $21 per helicopter. 

• Replacing all four nuts and bolts of 

an attachment fitting would require 4 

work-hours. Parts would cost $1,000 for 

a total cost of $1,340 per helicopter. 

• Replacing the attachment fitting or 

plate would require 16 work-hours 

respectively. Parts would cost $2,000 

respectively for a total cost of $3,360 to 

replace each part per helicopter. 

• Replacing frames 3855 and 5295 

would require 40 work-hours 

respectively. Parts would cost $5,000 to 

replace each frame for a total cost of 

$8,400 per frame 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. 

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: 


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34290 Federal Register / Vol. 78, No. 110 / Friday, June 7, 2013 / Proposed Rules 

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): 

EUROCOPTER FRANCE: Docket No. FAA– 

2013–0487; Directorate Identifier 2010– 

SW–056–AD. 

(a) Applicability 

This AD applies to Eurocopter France 

(Eurocopter) Model AS332L2 and EC225LP 

helicopters, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

loss of tightening torque of a bolt that secures 

the front and rear main gearbox (MGB) 

suspension bar attaching fittings, which can 

change the loads on the frames and cause 

cracking. This condition could lead to failure 

of the MGB supporting structure, detachment 

of the MGB, 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 

accomplished previously. 

(e) Required Actions 

(1) Within 500 hours time-in-service (TIS), 

and thereafter at intervals not to exceed 825 

hours TIS, inspect the tightening torque of 

each bolt that secures the front and rear MGB 

attaching fitting by using as reference Figure 

1 of Eurocopter Alert Service Bulletin (ASB) 

No. 05.00.65, Revision 0, dated March 28, 

2006, for the Model AS332L2 helicopters; 

and ASB No. 05A002, Revision 1, dated 

December 6, 2007, for the Model EC225LP 

helicopters. 

(2) If the loss of tightening torque of a nut 

is less than or equal to 20 percent of the 

minimum tightening torque, before further 

flight, readjust the tightening torque. 

(3) If the loss of tightening torque of any 

nut (front or rear) is greater than 20 percent 

of the minimum tightening torque, before 

further flight: 

(i) Inspect each bolt and nut that secures 

the attachment fitting for a crack, and 

(ii) Inspect for a crack in the attachment 

area of the attachment fitting, the attachment 

plate, and Frame 3855 for the front fitting 

and Frame 5295 for the rear fitting. 

(A) If no crack exists, readjust the 

tightening torque. 

(B) If there is a crack in any nut or bolt, 

before further flight, replace all four nuts and 

bolts of the affected attachment fitting. 

(C) If there is a crack in the attachment area 

of the attachment fitting or the attachment 

plate, before further flight, replace the 

cracked attachment fitting or plate with an 

airworthy fitting or plate. 

(D) If there is a crack in Frame 3855 for the 

front fitting or Frame 5295 for the rear fitting, 

before further flight, repair or replace the 

frame. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: 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. 

(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 

The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2006–0163 R1, dated December 13, 2007. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6330, Main Rotor Transmission Mount. 

Issued in Fort Worth, Texas, on May 29, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–13487 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–2013–0491; Directorate 

Identifier 2008–SW–012–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 430 helicopters. This 

proposed AD would require installing a 

placard on the instrument panel 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 steady-state operations. 

The proposed actions are intended to 

alert pilots to avoid certain engine 

speeds during steady-state 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 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1