Federal Register / Vol. 79, No. 21 / Friday, January 31, 2014 / Rules and Regulations 5251 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will 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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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 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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2014–02–02 Bell Helicopter Textron 

Canada Limited: Amendment 39–17730; 

Docket No. FAA–2013–0525; Directorate 

Identifier 2011–SW–063–AD. 

(a) Applicability 

This AD applies to Model 206L, L–1, L–3, 

and L–4 helicopters with a main rotor (M/R) 

blade, part number (P/N) 206–015–001–115, 

–117, –119, or –121, with a serial number (S/ 

N) listed in Table 1 or 2 of Bell Helicopter 

Alert Service Bulletin [No. 206L–09–163, 

Revision A, dated April 19, 2012 (ASB), 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

the manufacture of an M/R blade with an 

oversized spar spacer. This condition could 

result in failure of an M/R blade and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective March 7, 2014. 

(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) Actions Required 

Within 100 hours time-in-service (TIS): 

(1) For each M/R blade with an S/N listed 

in Table 1 of the ASB, measure the M/R blade 

spar spacer by following the 

Accomplishment Instructions, Part II A), 

paragraphs 1 through 3, of the ASB. If the 

spar spacer measures more than 1.018 inches 

(25.86 millimeters), reidentify the blade by 

following Part II A, paragraph 5.a. and Table 

3, of the ASB. 

(2) For each M/R blade with an S/N listed 

in Table 2 of the ASB, measure the M/R blade 

spar spacer by following the 

Accomplishment Instructions, Part II B, 

paragraphs 1 through 3, of the ASB. If the 

spar spacer measures more than 1.018 inches 

(25.86 millimeters), reidentify the blade by 

following Part II B, paragraph 5 and Table 4, 

of the ASB. 

(3) For each reidentified blade, reduce the 

life limit from 3,600 hours TIS to 2,300 hours 

TIS, and make an entry on the component 

history card or equivalent record. 

(4) Before further flight, remove any blade 

that exceeds the new retirement life of 2,300 

hours TIS. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Sharon Miles, 

Aerospace Engineer, FAA, Rotorcraft 

Directorate, Regulations and Policy Group, 

2601 Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5110, email 

sharon.y.miles@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 

Transport Canada Civil Aviation (TCCA) AD 

CF–2011–43, dated November 10, 2011. You 

may view the TCCA AD on the internet at 

http://www.regulations.gov in Docket No. 

FAA–2013–0525. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6210 Main Rotor Blades. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Bell Helicopter Alert Service Bulletin 

No. 206L–09–163, Revision A, dated April 

19, 2012. 

(ii) Reserved. 

(3) For Bell Helicopter 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/. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on January 15, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–01466 Filed 1–30–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0679; Directorate 

Identifier 2009–SW–015–AD; Amendment 

39–17733; AD 2014–02–05] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France (Eurocopter) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter Model AS350B, AS350BA, 

AS350B1, AS350B2, AS350B3, AS350C, 

AS350D, and AS350D1 helicopters. This 

AD requires measuring the distance 

between the end of the main rotor 

collective pitch lever (collective) 

locking stud (locking stud) and the 

locking strip and repairing the locking 

stud if the clearance is insufficient. This 


emcdonald on DSK67QTVN1PROD with RULES
5252 Federal Register / Vol. 79, No. 21 / Friday, January 31, 2014 / Rules and Regulations 

AD was prompted by a report that 

insufficient distance between the 

locking stud and the locking strip may 

cause the collective to become 

inadvertently locked in the low pitch 

(low) position. The actions of this AD 

are intended to prevent the collective 

from becoming inadvertently locked in 

the low position and subsequent loss of 

control of the helicopter. 

DATES: This AD is effective March 7, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of March 7, 2014. 

ADDRESSES: For service information 

identified in this 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. 

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 AD, the foreign 

authority’s AD, any incorporated-byreference service information, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (phone: 800–647–5527) is U.S. 

Department of Transportation, Docket 

Operations Office, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone 817–222–5110; email 

robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On August 5, 2013, at 78 FR 47230, 

the Federal Register published our 

notice of proposed rulemaking (NPRM), 

which proposed to amend 14 CFR part 

39 by adding an AD that would apply 

to Eurocopter Model AS350B, 

AS350BA, AS350B1, AS350B2, 

AS350B3, AS350C, AS350D, and 

AS350D1 helicopters. The NPRM 

proposed to require measuring the 

distance between the end of the 

collective locking stud and the locking 

strip and repairing the locking stud if 

the clearance is insufficient. The 

proposed requirements were intended to 

prevent the collective from becoming 

inadvertently locked in the low position 

and subsequent loss of control of the 

helicopter. 

The NPRM was prompted by AD No. 

2009–0019, dated February 3, 2009, 

issued by the European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for the Eurocopter Model 

AS350 helicopters. EASA advises that 

the clearance between the collective 

locking stud and the locking strip may 

be insufficient when the collective is 

positioned in the low pitch stop. During 

an autorotation test flight, the collective 

rubbed against the locking strip in the 

low pitch position. The rubbing was due 

to inadequate clearance and could result 

in the collective being inadvertently 

locked in the low pitch position. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (78 FR 47230, August 5, 2013). 

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 the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Differences Between This AD and the 

EASA AD 

The EASA AD does not apply to 

Model AS350C or AS350D1 helicopters, 

and this AD applies to these models 

because they have a similarly-designed 

collective pitch lock. The EASA AD 

applies to the Model AS350BB, and this 

AD does not because that model does 

not have a U.S. type certificate. This AD 

requires an initial inspection within 100 

hours time-in-service, while the EASA 

AD requires this inspection ‘‘after the 

last flight of the day.’’ 

Related Service Information 

Eurocopter issued Service Bulletin 

No. 67.00.37, Revision 2, dated 

December 2, 2008, originally issued on 

September 27, 2007, and also identified 

as modification (MOD) 073237, which 

contains procedures for replacing the 

locking stud on the collective levers 

with a new locking stud with higher 

wear resistance. The new locking stud is 

longer than the previous one and has 

reduced the distance between the 

locking stud and the locking strip. In 

some cases, the reduced distance is 

insufficient when the collective is 

positioned in the low pitch position 

causing the collective to lock in that 

position. As a result, Eurocopter has 

issued one Emergency Alert Service 

Bulletin (EASB), Revision 0, dated 

January 12, 2008, with two numbers. 

EASB No. 05.00.58 is for civil Model 

AS350B, BA, BB, B1, B2, B3, and D 

helicopters and military Model 

AS350L1 helicopters. EASB No. 

05.00.35 is for military Model AS550A2, 

C2, C3, and U2 helicopters. The EASB 

specifies measuring to ensure a required 

minimum distance between the locking 

stud and the locking strip and specifies 

a repair solution in case the distance is 

insufficient. As a precaution, Eurocopter 

extended the measure and repair to 

helicopters with locking studs before 

MOD 073237. Eurocopter also revised 

Service Bulletin No. 67.00.37 to include 

these procedures. 

Costs of Compliance 

We estimate that this AD will affect 

651 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs to comply with this AD. 

We estimate 1 work hour to measure the 

clearance and repair the locking stud 

and locking strip at $85 per work hour. 

Required parts will cost $95 per 

helicopter. Based on these estimates, the 

total cost per helicopter will be $180, 

and the total cost for the fleet will be 

$117,180. 

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 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 79, No. 21 / Friday, January 31, 2014 / Rules and Regulations 5253 

because it addresses an unsafe condition 

that is likely to exist or develop on 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will 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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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 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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2014–02–05 Eurocopter France Helicopters: 

Amendment 39–17733; Docket No. 

FAA–2013–0679; Directorate Identifier 

2009–SW–015–AD. 

(a) Applicability 

This AD applies to Eurocopter Model 

AS350B, AS350BA, AS350B1, AS350B2, 

AS350B3, AS350C, AS350D, and AS350D1 

helicopters, certificated in any category, 

without modification (MOD) 073175 

installed; with MOD 073237 installed in 

accordance with Eurocopter Service Bulletin 

No. 67.00.37, Revision 0, dated September 

27, 2007, or Revision 1, dated February 6, 

2008; or with one of the following serial 

numbers: 3972, 3973, 3982, 3987, 4003, 4023, 

4046, 4050, 4086, 4120, 4122, 4132, 4143, 

4152, 4172, 4194, 4259, 4314, 4324, 4378, 

4392, 4447, 4452, 4477, 4489, 4490, 4501, 

4523, 4546, 4560, 4589, 4594, 4599, 4632, 

4659, 4666, or 4671. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

the main rotor collective pitch lever 

(collective) locking stud (locking stud) 

inadvertently locking in the low pitch (low) 

position, which could result in subsequent 

loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective March 7, 2014. 

(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 

(1) For helicopters with MOD 073237 

installed, within 100 hours time-in-service 

(TIS): 

(i) With the collective (item b) in the low 

position but not locked on the locking strip 

(item a), measure the distance between the 

end of the locking stud (item c) and the 

locking strip as indicated by dimension ‘‘J’’ 

in Figure 2 of Eurocopter Emergency Alert 

Service Bulletin No. 05.00.58, Revision 0, 

dated January 12, 2008 (EASB 05.00.58). 

(ii) If the distance between the end of the 

locking stud and the locking strip is equal to 

or more than 3 millimeters (mm), no further 

action is required. 

(iii) If the distance between the end of the 

locking stud and the locking strip is less than 

3 mm and MOD 073175 is not installed, 

inspect to determine whether the grommet in 

the locking strip is seated against the console 

as shown in Figure 2 of EASB 05.00.58. 

(A) If the grommet is not seated against the 

console, restore the original profile of the 

locking strip by doing the following: 

(1) Clamp the locking strip in a vice with 

soft jaws and apply load progressively to the 

locking strip to restore the original profile of 

the locking strip. 

(2) With the collective in the low position 

but not locked on the locking strip, measure 

the distance between the end of the locking 

stud and the locking strip as indicated by 

dimension ‘‘J’’ in Figure 2 of EASB 05.00.58. 

(3) If the distance between the end of the 

locking stud and the locking strip is equal to 

or more than 3 mm, no further action is 

required. 

(4) If the distance between the end of the 

locking stud and the locking strip is less than 

3 mm, adjust the length of the locking stud 

and re-identify the locking stud by following 

the Accomplishment Instructions, paragraph 

2.B.2.c., of EASB 05.00.58, except you are not 

required to comply with paragraph 2.B.4 of 

EASB 05.00.58. 

(B) If the grommet is seated against the 

console, adjust the length of the locking stud 

and re-identify the locking stud by following 

the Accomplishment Instructions, paragraph 

2.B.2.c, of EASB 05.00.58, except you are not 

required to comply with paragraph 2.B.4 of 

EASB 05.00.58. 

(iv) If the distance between the end of the 

locking stud and the locking strip is less than 

3 mm and MOD 073175 is installed, adjust 

the length of the locking stud and re-identify 

the locking stud by following the 

Accomplishment Instructions, paragraph 

2.B.2.c., of EASB 05.00.58, except you are not 

required to comply with paragraph 2.B.4 of 

EASB 05.00.58. 

(v) After adjusting the length of the locking 

stud in accordance with paragraph 2.B.2.c of 

the EASB, determine whether the distance 

between the end of the locking stud and the 

locking strip is equal to or more than 3 mm. 

(A) If the distance between the end of the 

locking stud and the locking strip is equal to 

or more than 3 mm, no further action is 

required. 

(B) If the distance between the end of the 

locking stud and the locking strip is less than 

3 mm, do not approve the helicopter for 

return to service until the distance between 

the end of the locking stud and the locking 

strip is equal to or more than 3 mm. 

(2) For helicopters without MOD 073237 

installed, within 100 hours TIS: 

(i) With the collective in the low position 

but not locked on the locking strip, measure 

the distance between the end of the locking 

stud and the locking strip as indicated by 

dimension ‘‘J’ in Figure 2 of EASB 05.00.58. 

(ii) If the distance between the end of the 

locking stud and the locking strip is equal to 

or more than 3 mm, no further action is 

needed. 

(iii) If the distance between the end of the 

locking stud and the locking strip is less than 

3 mm and MOD 073175 is not installed, 

inspect to determine whether the grommet in 

the locking strip is seated against the console 

as shown in Figure 2 of EASB 05.00.58. 

(A) If the grommet is not seated against the 

console, restore the original profile of the 

locking strip by doing the following: 

(1) Clamp the locking strip in a vice with 

soft jaws and apply load progressively to the 

locking strip. 

(2) With the collective in the low position 

but not locked on the locking strip, measure 

the distance between the end of the locking 

stud and the locking strip as indicated by 

dimension ‘‘J’’ in Figure 2 of the EASB 

05.00.58. 

(3) If the distance between the end of the 

locking stud and the locking strip is equal to 

or more than 3 mm, no further action is 

required. 

(4) If the distance between the end of the 

locking stud and the locking strip is less than 

3 mm, do not approve the helicopter for 

return to service until the distance between 

the end of the locking stud and the locking 

strip is equal to or more than 3 mm. 

(B) If the grommet is seated against the 

console, do not approve the helicopter for 

return to service until the distance between 

the end of the locking stud and the locking 

strip is equal to or more than 3 mm. 

(iv) If the distance between the end of the 

locking stud and the locking strip is less than 

3 mm and MOD 073175 is installed, do not 

approve the helicopter for return to service 

until the distance between the end of the 

locking stud and the locking strip is equal to 

or more than 3 mm. 


emcdonald on DSK67QTVN1PROD with RULES
5254 Federal Register / Vol. 79, No. 21 / Friday, January 31, 2014 / Rules and Regulations 

(3) Repeat the measurement requirement in 

paragraphs (e)(1) or (e)(2) of this AD as 

applicable to your helicopter each time the 

collective, locking stud, or locking strip is 

replaced; each time the locking strip setting 

is readjusted; or at intervals not exceeding 

660 hours TIS or 2 years, whichever occurs 

first. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone 817–222– 

5110; email robert.grant@faa.gov. 

(2) For operations conducted under 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) Eurocopter Service Bulletin (SB) No. 

67.00.21, Revision 1, dated June 21, 2006, 

and SB No. 67.00.37, Revision 2, dated 

December 2, 2008, which are not 

incorporated by reference, contain additional 

information about the subject of this AD. For 

service information identified in this 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. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2009–0019, dated February 3, 2009. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA–2013–0679. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6710 Main Rotor Control. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Eurocopter Emergency Alert Service 

Bulletin No. 05.00.58, Revision 0, dated 

January 12, 2008. 

(ii) Reserved. 

Note 1 to paragraph (i)(2): Eurocopter 

Emergency Alert Service Bulletin (EASB) No. 

05.00.58, Revision 0, dated January 12, 2008, 

is co-published in one document with 

Eurocopter EASB No. 05.00.35, Revision 0, 

dated January 12, 2008, which is not 

incorporated by reference in this AD. 

(3) For Eurocopter service information 

identified in this 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. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on January 16, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–01467 Filed 1–30–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0611; Directorate 

Identifier 2013–CE–019–AD; Amendment 

39–17731; AD 2014–02–03] 

RIN 2120–AA64 

Airworthiness Directives; Beechcraft 

Corporation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2011–27– 

51 for certain Beechcraft Corporation 

Models 1900, 1900C, and 1900D 

airplanes. AD 2011–27–51 required 

inspecting the elevator bob-weight and 

attaching linkage for correct installation 

and for damage or deformation to the 

weight and/or weight bracket with 

corrective action as necessary. This AD 

requires installation of the secondary 

elevator bob-weight stop bolt. The 

elevator bob-weight (stabilizer weight) 

traveling past its stop bolt may allow the 

attaching linkage to move over-center 

and lead to reduced nose down elevator 

control. We are issuing this AD to 

correct the unsafe condition on these 

products. 

DATES: This AD is effective March 7, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 7, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of January 18, 2012 (77 FR 

2439, January 18, 2012). 

ADDRESSES: For service information 

identified in this AD, contact Beechcraft 

Corporation at P.O. Box 85, Wichita, 

Kansas 67201–0085; telephone: (800) 

429–5372 or (316) 676–3140; Internet: 

http://www.beechcraft.com. Beechcraft 

Corporation publishes service 

information for the Beechcraft 

Corporation airplanes affected by this 

AD action. You may review copies of 

the referenced service information at the 

FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call (816) 329– 

4148. 

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–2013– 

0611; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Don 

Ristow, Aerospace Engineer, Wichita 

Aircraft Certification Office, FAA, 1801 

Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: (316) 946– 

4120; fax: (316) 946–4107; email: 

donald.ristow@faa.gov. 

SUPPLEMENTARY INFORMATION:

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2011–27–51, 

Amendment 39–16915 (77 FR 2439, 

January 18, 2012), (‘‘AD 2011–27–51’’). 

AD 2011–27–51 applied to certain 

Beechcraft Corporation Models 1900, 

1900C, and 1900D airplanes. The NPRM 

published in the Federal Register on 

July 17, 2013 (78 FR 42724). The NPRM 

proposed to retain all of the 

requirements of AD 2011–27–51 and 

add the requirement to install the 

secondary elevator bob-weight stop bolt, 

Kit 114–5060. We are issuing this AD to 


emcdonald on DSK67QTVN1PROD with RULES