Federal Register / Vol. 77, No. 186 / Tuesday, September 25, 2012 / Proposed Rules 58973 

shelf reinforcement kit per helicopter at 

an average labor rate of $85 per work 

hour. Required parts would cost about 

$2,560 per helicopter. Based on these 

figures, we estimate the total cost of the 

proposed AD on U.S. operators to be 

$74,480 to reinforce the shelf of the 

entire 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): 

Eurocopter France: Docket No. FAA–2012– 

1014; Directorate Identifier 2010–SW– 

058–AD. 

(a) Applicability 

This AD applies to Model SA–365N1, AS– 

365N2, and AS 365 N3 helicopters, with the 

GV76–1 vertical gyro unit installed on the 

left-hand (LH) or right-hand (RH) shelf in the 

rear cargo compartment, pre-MOD 

365P081895, certificated in any category, all 

serial numbers except 6698, 6701, 6723, 

6737, and 6741. 

(b) Unsafe Condition 

This AD defines the unsafe condition as an 

undetected flight display error of a slow drift 

in the roll axis. This condition could result 

in disorientation of the pilot 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) Before further flight, revise the 

Limitations section of the Rotorcraft Flight 

Manual (RFM) by inserting a copy of this AD 

into the RFM or by pen and ink changes to 

the RFM that prohibits flight in instrument 

meteorological conditions (IMC) or night 

visual flight rules (VFR) for each helicopter 

with a vertical gyro unit GV76–1 installed on 

the rear cargo compartment shelf without 

reinforcement per Modification 365P081895. 

(2) Within 110 hours time-in-service, 

modify the GV76–1 vertical gyro unit shelf as 

depicted in Figures 1 through 3 and by 

following the Accomplishment Instructions, 

paragraphs 2.A. through 2.B.2.e., of 

Eurocopter Alert Service Bulletin No. 

34.00.31, Revision 1, dated July 28, 2010. 

After reinforcing the shelf, operationally test 

the GV76–1 vertical gyro unit and 

functionally test the navigation systems. 

(3) After modifying the GV76–1 vertical 

gyro unit shelf, remove this AD from the 

Limitations section of the RFM or remove 

any changes to the Limitations section of the 

RFM that prohibit flight in IMC or VFR as a 

result of paragraph (d)(1) of this AD. 

(4) Modifying the GV76–1 vertical gyro 

unit shelf is terminating action for the 

requirements of this AD. 

(e) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Mark F. Wiley, 

Aviation Safety Engineer, Rotorcraft 

Directorate, Regulations and Policy Group, 

2601 Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5134; email 

mark.f.wiley@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. 

(f) Additional Information 

(1) For service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, TX 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. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2010–0100R1, dated August 4, 2010, and 

corrected August 11, 2010. 

(g) Subject 

Joint Aircraft System/Component (JASC) 

Code: 3421: Attitude Gyro and Indicator 

System. 

Issued in Fort Worth, Texas, on September 

14, 2012. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–23444 Filed 9–24–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1015; Directorate 

Identifier 2007–SW–069–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 the 

Eurocopter France (Eurocopter) Model 

AS332C, AS332L, and AS332L1 

helicopters. This proposed AD is 

prompted by reports of electro-valve 


emcdonald on DSK67QTVN1PROD with PROPOSALS
58974 Federal Register / Vol. 77, No. 186 / Tuesday, September 25, 2012 / Proposed Rules 

power supply disruptions while a 

helicopter is on the ground, causing the 

landing gear to retract and the 

helicopter nose to drop. This results in 

damage to the forward section of the 

helicopter’s bottom structure. This 

proposed AD would require modifying 

the main landing gear control panel 

(control panel) 33G, connector 100G, 

and wiring. It also would require tests 

to ensure that these modifications 

function correctly. We propose this AD 

to prevent an uncommanded landing 

gear retraction that would cause the 

helicopter nose to drop and hit the 

ground while the rotor blades are 

spinning. 

DATES: We must receive comments on 

this proposed AD by November 26, 

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 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 a copy of 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: 

George Schwab, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, 

Safety Management Group, 2601 

Meacham Blvd., Fort Worth, Texas, 

76137; telephone: (817) 222–5114; fax: 

(817) 222–5961; email: 

george.schwab@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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued AD No. 2006–0152, 

dated May 30, 2006 (AD 2006–0152), to 

correct an unsafe condition for the 

Eurocopter Model AS 332 C, AS 332 C1, 

AS 332 L, and AS 332 L1 helicopters 

with a control panel 33G, part number 

(P/N) 332A67–1623–00, –06, –0610, or 

–0651. EASA advises of electro-valve 

power supply disruptions, which 

caused the landing gear to retract and 

the helicopter to drop, resulting in 

damage to the forward section of the 

helicopter’s bottom structure. AD 2006– 

0152 requires compliance with 

Eurocopter Alert Service Bulletin (ASB) 

No. 32.00.18, Revision 1, dated March 

27, 2006, or later revisions. AD 2006– 

0152 supersedes Direction Generale de 

L’Aviation Civile France AD No. F– 

2005–100, dated June 22, 2005 (AD No. 

F–2005–100), which required 

compliance with ASB No. 32.00.18, any 

approved revision. 

FAA’s Determination 

These helicopter models 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 

above. We are proposing this AD 

because we evaluated all known 

relevant information and determined 

that an unsafe condition exists and is 

likely to exist or develop on other 

products of these same type designs. 

Related Service Information 

We reviewed Eurocopter ASB No. 

32.00.18, Revision 2, dated July 12, 

2010, for Model AS332C, AS332C1, 

AS332L, and AS332L1 helicopters and 

military Model AS332B, AS332B1, 

AS332M, AS332M1, AS332F1 

helicopters with the specified control 

panel 33G. That ASB states that 

electrical interferences on the solenoid 

valve power supply line have caused 

untimely retraction of the main landing 

gear, causing helicopters to sink, 

resulting in damage to the front section 

of the helicopter’s bottom structure. The 

ASB describes procedures for modifying 

the main landing gear control tab on the 

control panel 33G, replacing the fixed 

connector on the control panel 33G, 

replacing the removable connector on 

the corresponding wiring, and testing 

the affected systems to ensure that these 

modifications function correctly. The 

ASB states that these actions are 

intended to prevent untimely power 

supply to the solenoid valve when the 

main landing gear control tab is on 

‘‘extended’’ and to avoid main landing 

gear retraction. AD No. 2006–0152 

classified portions of the ASB as 

mandatory. 

Proposed AD Requirements 

This proposed AD would require, 

within 90 days, modifying the control 

panel 33G, connector 100G, and wiring, 

and determining that these 

modifications are functioning correctly 

by conducting specific tests. The 

proposed actions would be 

accomplished in accordance with the 

specified portions of the ASB No. 

32.00.18, Revision 2, dated July 12, 

2010. 

Differences Between This Proposed AD 

and the EASA AD 

This proposed AD differs from the 

EASA AD as follows: 

• This proposed AD requires 

compliance within 90 days, while the 

EASA AD requires compliance within 3 

months. The EASA AD also addresses 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 186 / Tuesday, September 25, 2012 / Proposed Rules 58975 

spare parts, and this proposed AD does 

not address spare parts. 

• The EASA AD requires a repeat of 

the tests for helicopters that have been 

modified in compliance with AD F– 

2005–100, and this proposed AD does 

not. 

• The EASA AD also applies to the 

Model AS332C1 helicopter, and this 

proposed AD does not because this 

model does not have an FAA-issued 

type certificate. 

Costs of Compliance 

We estimate that this proposed AD 

would affect three helicopters of U.S. 

registry. We estimate the following costs 

to comply with this proposed AD: 

We estimate that modification of the 

control panel, connector, and wiring 

would take one work hour to complete 

at $85 per hour, and that parts would 

cost $293. Performing function tests 

would take about 4.5 hours to complete, 

for a total labor cost of $383. Thus, we 

estimate a total cost per helicopter of 

$761, and a total cost of $2,283 for the 

fleet. 

We do not control warranty coverage. 

Accordingly, we have included all costs 

in our cost estimate. 

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): 

Eurocopter France (Eurocopter): Docket No. 

FAA–2012–1015; Directorate Identifier 

2007–SW–069–AD. 

(a) Applicability 

This AD applies to Eurocopter Model 

AS332C, AS332L, and AS332L1 helicopters 

not modified per modification (MOD) 

0723817, MOD 0725670, MOD 332P083218 

or MOD 332A088381, with a main landing 

gear control panel (control panel) 33G, part 

number (P/N) 332A67–1623–00, -06, -0610, 

or -0651; certificated in any category. 

(b) Unsafe Condition 

This AD is defines the unsafe condition as 

an uncommanded landing gear retraction, 

which could cause the helicopter nose to 

drop and hit the ground while the rotor 

blades are spinning. 

(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 

Within 90 days, modify the control panel 

33G and connector 100G, route the 

1GA5103E wiring, and perform the tests in 

accordance with the Accomplishment 

Instructions, Paragraphs 2.B 2.a. through 

2.B.3.d., and as depicted in Figures 1 and 2, 

of Eurocopter Alert Service Bulletin No 

32.00.18, Revision 2, dated July 12, 2010. 

(e) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Rotorcraft Directorate, 

Safety Management Group, 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 ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(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. 

(f) Additional Information 

(1) 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 a copy of the 

referenced service information at the FAA, 

Office of the Regional Counsel, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

the European Aviation Safety Agency AD No. 

2006–0152, dated May 30, 2006. 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 3230, landing gear retract/extend 

system. 

Issued in Fort Worth, Texas, on September 

14, 2012. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–23460 Filed 9–24–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE INTERIOR 

Office of Surface Mining Reclamation 

and Enforcement 

30 CFR Part 938 

[PA–161–FOR; Docket ID: OSM–2012–0009] 

Pennsylvania Regulatory Program 

AGENCY: Office of Surface Mining 

Reclamation and Enforcement (OSM), 

Interior. 


emcdonald on DSK67QTVN1PROD with PROPOSALS