63262 Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules 

Robinson Helicopter Company: Docket No. 

FAA–2012–1088; Directorate Identifier 

2012–SW–005–AD. 

(a) Applicability 

This AD applies to Robinson Helicopter 

Company (Robinson) Model R44 and R44 II 

helicopters with emergency floats equipped 

with an inflation valve assembly, part 

number (P/N) D757–1, not engraved with 

‘‘D758–4’’ or modified with modification 

B900–8, and containing a housing assembly, 

P/N D758–1, Revision C or prior, certificated 

in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

binding of the needle within the float 

inflation valve assembly, which has resulted 

in the emergency floats failing to inflate. 

(c) Comments Due Date 

Comments are due December 17, 2012. 

(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 Action 

Within 1 year or 500 hours time-in-service 

(TIS), whichever occurs first, replace the 

inflation valve assembly with an airworthy 

inflation valve assembly, P/N D757–1R. 

(f) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Los Angeles Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Venessa Stiger, Aerospace Engineer, Cabin 

Safety/Mechanical & Environmental Systems, 

Los Angeles Aircraft Certification Office, 

Transport Airplane Directorate, FAA, 3960 

Paramount Blvd., Lakewood, CA 90712– 

4137; telephone (562) 627–5337; email 

venessa.stiger@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 

Robinson R44 Service Bulletin SB–80, 

dated September 7, 2011, which is not 

incorporated by reference, contains 

additional information about the subject of 

this AD. For service information identified in 

this AD, contact Robinson Helicopter 

Company, 2901 Airport Drive, Torrance, CA 

90505; telephone (310) 539–0508; fax (310) 

539–5198; or at http:// 

www.robinsonheli.com/servelib.htm. You 

may review a copy of information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 3212, Emergency Flotation Section. 

Issued in Fort Worth, Texas, on October 2, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–25428 Filed 10–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1087; Directorate 

Identifier 2009–SW–32–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 (ECF) Model 

AS332C, L, and L1 helicopters to 

require an initial and repetitive 

inspections of the outer skin, butt strap, 

and fuselage frame for a crack and 

modification of the helicopter. This 

proposed AD is prompted by an AD 

issued by the European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Union, which states that a 

crack was discovered in a fuselage frame 

during a daily check. The proposed 

actions are intended to detect a crack, to 

prevent loss of airframe structural 

integrity and subsequent loss of control 

of the helicopter. 

DATES: We must receive comments on 

this proposed AD by December 17, 

2012. 

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 Forum 

Drive, Grand Prairie, Texas 75053–4005; 

telephone (800) 232–0323; fax (972) 

641–3710; or at http:// 

www.eurocopter.com. 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 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

EASA has issued EASA AD No. 2008– 

0035–E, dated February 21, 2008, to 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules 63263 

correct an unsafe condition for ECF 

Model AS 332 C, C1, L, and L1 

helicopters. 

The EASA AD states that a crack was 

discovered on an ECF Model AS332L 

helicopter in fuselage frame 5295, 

which has plates and angles assembled 

by riveting that corresponds to the first 

generation frame (before modification 

(MOD) 0722907). The crack in the frame 

was found because of a crack in the 

outer skin and in the butt strap where 

the rail of the main gear box (MGB) 

sliding cowling is attached to the frame. 

You may obtain further information by 

examining the EASA AD and any 

related service information in the AD 

docket. 

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 

Eurocopter has issued Alert Service 

Bulletin No. 05.00.76, Revision 0, dated 

February 20, 2008 (ASB), which 

specifies checking for a crack on the 

outside of the helicopter, on the skin 

and the butt strap near the sliding 

cowling rail attachment. If a crack is 

found in the outer skin or butt strap, the 

ASB specifies visually checking for a 

crack in Frame 5295. The ASB specifies 

doing MOD 0726478R2, which consists 

of cutting out a section of the sliding 

cowling rails. This cut-out exposes the 

splice near the rail attachment holes, 

making it easier to detect a crack in the 

frame during the 10-hour repetitive 

inspection and thus reducing the risks 

of a crack going undetected in Frame 

5295. Also, the ASB specifies contacting 

the manufacturer for the ‘‘appropriate 

repair sheet according to how the crack 

is situated’’ if there is a crack in Area 

1 of Frame 5295. EASA classified this 

ASB as mandatory and issued AD No. 

2008–0035–E, dated February 21, 2008, 

to ensure the continued airworthiness of 

these helicopters. 

Proposed AD Requirements 

This proposed AD would require 

compliance with specified portions of 

the manufacturer’s service bulletin 

including: 

• Within 10 hours time-in-service 

(TIS) for helicopters that have 8,800 or 

more hours TIS or before or upon 

reaching 8,810 hours TIS for helicopters 

that have less than 8,800 hours TIS, and 

thereafter at intervals not to exceed 10 

hours TIS, visually inspect for a crack 

in the outer skin and the butt strap in 

the sliding cowling right-hand and lefthand rail attachment areas on Frame 

5295. 

Æ If there is a crack in the outer skin 

or in the butt strap, before further flight, 

inspect for a crack in Frame 5295. 

Æ If there is a crack in the outer skin, 

butt strap, or Frame 5295, repair the part 

before further flight. 

• Within 300 hours TIS, modify each 

helicopter that has 8,800 or more hours 

TIS by doing MOD 0726478R2 on the 

sliding cowling rails and shims in the 

attachment areas on Frame 5295. 

Differences Between This Proposed AD 

and the EASA AD 

This proposed AD requires you to 

repair Frame 5295 before further flight 

rather than contacting the manufacturer. 

This proposal refers to a check as an 

inspection to be performed by a 

mechanic versus a check that a pilot can 

do if specifically allowed by the AD. 

This proposal also does not list the 

Model AS332C1 in the applicability 

because this model is not type 

certificated in the U.S. This proposed 

AD also does not allow further flight 

with the outer skin or butt strap cracked 

unless it is a ferry flight to a repair 

facility. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 5 helicopters of U.S. 

Registry. We estimate that it would take 

about 4.25 work-hours per helicopter to 

initially inspect for a crack and to 

modify the MGB sliding cowling rails. 

Each 10-hour repetitive inspection 

would take about 0.25 work-hour. The 

average labor rate is $85 per work-hour 

and required parts would cost about 

$1,793 per helicopter. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators would 

be $17,145 or $3,429 per helicopter, 

assuming 60 repetitive inspections 

would be performed each year and 

assuming the entire fleet is modified 

and no cracks are found. 

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. 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
63264 Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Eurocopter France: Docket No. FAA–2012– 

1087; Directorate Identifier 2009–SW– 

32–AD. 

(a) Applicability 

This AD applies to all Model AS332C, L, 

and L1 helicopters without modification 

(MOD) 0722907, except helicopters with 

serial numbers 2078 and 2102, certificated in 

any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the outer skin, butt strap, or fuselage 

frame, which could result in loss of airframe 

structural integrity, and subsequent loss of 

control of the helicopter. 

(c) 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. 

(d) Required Actions 

(1) Within 10 hours time-in-service (TIS) 

for helicopters that have 8,800 or more hours 

TIS or before or upon reaching 8,810 hours 

TIS for helicopters that have less than 8,800 

hours TIS, and thereafter at intervals not to 

exceed 10 hours TIS, visually inspect for a 

crack on the outer skin and the butt strap in 

the sliding cowling right-hand and left-hand 

rail attachment areas on Frame 5295 as 

shown in Figure 2 of Eurocopter Alert 

Service Bulletin No. 05.00.76, Revision 0, 

dated February 20, 2008 (ASB). 

(i) If there is a crack in the outer skin or 

in the butt strap per paragraph (d)(1) of this 

AD, before further flight, inspect for a crack 

in Frame 5295 in the areas shown in Figure 

3, Area 1, and Figure 4, of the ASB. 

(ii) If there is a crack in the outer skin, the 

butt strap, or in Frame 5295 in the areas 

inspected as required by this AD, before 

further flight, repair the part in accordance 

with a method approved by the FAA. 

(2) Within 300 hours TIS, for each 

helicopter that has 8,800 or more hours TIS, 

modify the sliding cowling rails and shims in 

the attachment areas on Frame 5295 

(corresponds to MOD 0726478R2), as 

depicted in Figure 5 and by following the 

Accomplishment Instructions, paragraph 

2.B.3., of the ASB. 

(e) Special Flight Permit 

A special flight permit is permitted for a 

helicopter with a crack in the outer skin or 

butt strap to operate the helicopter to a 

location where the requirements of this AD 

can be accomplished. A special flight permit 

is not permitted for a helicopter with a crack 

in Frame 5295. 

(f) Alternative Methods of Compliance 

(AMOC) 

(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 (France) 

AD No. 2008–0035–E, dated February 21, 

2008. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5311, Fuselage, Main Frame. 

Issued in Fort Worth, Texas, on October 2, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–25429 Filed 10–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1074; Directorate 

Identifier 2012–NM–027–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A330–200 Freighter series 

airplanes; Model A330–200 and –300 

series airplanes; and Model A340–200 

and –300 series airplanes. This 

proposed AD was prompted by a report 

of a manufacturing defect in certain rods 

installed in the belly fairing, which 

could lead to cracks at the crimped end 

of the rod. This proposed AD would 

require an inspection of the rods to 

determine the manufacturer; and for 

affected parts, an inspection for any 

cracking of the rods, and related 

investigative and corrective actions if 

necessary. We are proposing this AD to 

detect and correct cracking of the rods, 

which could result in rupture of rods 

that attach the belly fairing to the 

airframe, leading to separation of the 

belly fairing from the airframe, and 

consequent damage to airplane structure 

and airplane systems. 

DATES: We must receive comments on 

this proposed AD by November 30, 

2012. 

ADDRESSES: You may send comments 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 proposed AD, contact Airbus SAS— 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 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; 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 

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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1138; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1