1 

[Federal Register Volume 78, Number 156 (Tuesday, August 13, 2013)] 

[Rules and Regulations] 

[Pages 49115-49116] 

From the Federal Register Online via the Government Printing Office [www.gpo.gov] 

[FR Doc No: 2013-19444] 

–––––––––––––––––––––––––––––––––– 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA-2012-1297; Directorate Identifier 2012-SW-100-AD; Amendment 39-17285; 

AD 2012-25-04] 

RIN 2120-AA64 

Airworthiness Directives; Eurocopter France Helicopters 

AGENCY: Federal Aviation Administration (FAA), DOT. 

ACTION: Final rule; correction. 

–––––––––––––––––––––––––––––––––– 

SUMMARY: The FAA is correcting an airworthiness directive (AD) that was published in the 

Federal Register. The AD applies to certain Eurocopter France (Eurocopter) Model AS350B3 

helicopters. The reference to Title 14, Code of Federal Regulations (14 CFR) 91.173 in the Required 

Actions section is incorrect. This document corrects that error. In all other respects, the original 

document remains the same. 

DATES: This final rule is effective August 13, 2013. The effective date for AD 2012-25-04 (78 FR 

24041, April 24, 2013) remains May 9, 2013. 

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov; 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: Robert Grant, Aviation Safety Engineer, 

Rotorcraft Directorate, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, TX 

76137; phone: (817) 222-5110; fax: (817) 222-5110; email: robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: AD 2012-25-04, Amendment 39-17285 (78 FR 24041, 

April 24, 2013), applies to certain Eurocopter Model AS350B3 helicopters. AD 2012-25-04 currently 

requires, in part, before further flight and thereafter after each flight without exceeding 3 hours timein-service between two checks, visually checking each laminated half bearing for certain conditions, 

and allows this check to be performed by a pilot if certain regulatory recordkeeping requirements are 

AD To Be Superseded
2 

met. As such, AD 2012-25-04 currently includes the following as the last sentence under paragraph 

(f)(4): ''The record must be maintained as required by 14 CFR 91.173, 121.380, or 134.439.'' 

 As published, the reference to 14 CFR 91.173 is incorrect. The correct reference is to 14 CFR 

91.417. 

 No other part of the preamble or regulatory information has been changed; therefore, only the 

changed portion of the final rule is being published in the Federal Register. 

Correction of Regulatory Text 

§ 39.13 [Corrected] 

 In the Federal Register of April 24, 2013, on page 24046, in the second column, the last sentence 

of paragraph (f)(4) is corrected to read as follows: 

* * * * * 

 The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439. 

* * * * * 

 Issued in Fort Worth, Texas, on August 2, 2013. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

AD To Be Superseded
3 

[Federal Register Volume 78, Number 79 (Wednesday, April 24, 2013)] 

[Rules and Regulations] 

[Pages 24041-24047] 

From the Federal Register Online via the Government Printing Office [www.gpo.gov] 

[FR Doc No: 2013-09420] 

–––––––––––––––––––––––––––––––––– 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA-2012-1297; Directorate Identifier 2012-SW-100-AD; Amendment 39-17285; 

AD 2012-25-04] 

RIN 2120-AA64 

Airworthiness Directives; Eurocopter France Helicopters 

AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). 

ACTION: Final rule; request for comments. 

–––––––––––––––––––––––––––––––––– 

SUMMARY: We are superseding an existing emergency airworthiness directive (EAD) for 

Eurocopter France (Eurocopter) Model AS350B3 helicopters with certain part-numbered laminated 

half-bearings (bearings) and tail rotor (T/R) blades installed. The existing EAD currently requires 

installing two placards and revising the Rotorcraft Flight Manual (RFM). The EAD also requires 

certain checks and inspecting and replacing, if necessary, all four bearings. Finally, the EAD requires 

a one-time removal and inspection of the bearings, and replacing the bearings if necessary. Since we 

issued that EAD, we have determined that newly-designed helicopters with other part-numbered T/R 

blades may be affected by this unsafe condition and that the requirements should allow the bearing 

removal and inspection to be performed before the last flight of the day. This superseding AD 

removes the bearing and T/R blade part numbers (P/N) from the applicability paragraph and clarifies 

when the bearing removal and inspection is required. The actions are intended to prevent vibration 

due to a failed bearing, failure of the T/R, and subsequent loss of control of the helicopter. 

DATES: This AD becomes effective May 9, 2013. 

 We must receive comments on this AD by June 24, 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. 

AD To Be Superseded
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• 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 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 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: 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: 

Comments Invited 

 This AD is a final rule that involves requirements affecting flight safety, and we did not provide 

you with notice and an opportunity to provide your comments prior to it becoming effective. 

However, 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 resulted from adopting this AD. The most helpful comments reference a specific portion 

of the AD, 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 them 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 rulemaking during the comment 

period. We will consider all the comments we receive and may conduct additional rulemaking based 

on those comments. 

Discussion 

 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member 

States of the European Union, has issued EASA Emergency AD No. 2012-0207-E, dated October 5, 

2012 (EAD 2012-0207-E), to correct an unsafe condition for Eurocopter Model AS 350 B3 

helicopters modified by Modification (MOD) 07 5601. MOD 07 5601 is an integral part of a specific 

Model AS350B3 configuration, commercially identified as ‘‘AS350B3e'' and is not fitted on Model 

AS350B3 helicopters of other configurations. EASA advises that premature failures of bearings, P/N 

704A33-633-261, installed in combination with T/R blades P/N 355A12.0055.00 or 355A12.0055.01, 

have recently been detected on AS 350 B3 helicopters in ‘‘AS350B3e'' configuration. Three cases of 

vibrations originating from the T/R, caused by failure of the bearings, were reported, which were 

detected in flight. Subsequently, an accident occurred in which the pilot felt strong vibrations from 

the T/R before losing control of the helicopter. An investigation revealed that prior to the accident, 

the bearings had been replaced twice on the helicopter due to deterioration. EASA EAD 2012-0207-E 

requires installing placards and changing the RFM to limit the flight envelope by reducing the 

Velocity Never Exceed (VNE) true airspeed (TAS) limitation to reduce the dynamic loads on the 

AD To Be Superseded
5 

T/R, a one-time pre-flight inspection and repetitive post-flight inspections of the bearings to detect 

damage, a one-time ‘‘After Last Flight of the day'' (ALF) inspection (including T/R disassembly), 

and replacing all bearings if any bearing is damaged. 

 On October 17, 2012, we issued EAD No. 2012-21-51 for Eurocopter Model AS350B3 

helicopters with MOD 07 5601, with bearing P/N 704A33-633-261 in combination with tail rotor 

blade P/N 355A12.0055.00 or 355A12.0055.01, installed. We sent that EAD to all known U.S. 

owners and operators of these helicopters. That EAD requires, before further flight, installing two 

placards on the instrument panel and revising the RFM to reduce the VNE indicated airspeed (IAS) 

limitation. It also requires, before further flight and thereafter after each flight, visually checking all 

visible faces of the bearings for separation, a crack, or an extrusion, and replacing the four bearings if 

there is an extrusion or if there is a separation or a crack on the pressure side bearing greater than 5 

millimeters (.196 inches). Lastly, the EAD requires, after the last flight of the day, performing a onetime inspection of the bearings for a separation, a crack, or an extrusion, and replacing the four 

bearings if there is a separation, crack, or extrusion. Our EAD differed from EASA EAD 2012-0207-

E in that the EASA EAD placard limited TAS, while the placard in our EAD limited IAS. 

Actions Since Existing EAD Was Issued 

 Since we issued EAD 2012-21-51, EASA issued EAD No. 2012-0217-E, dated October 19, 2012 

(EAD 2012-0217-E), which superseded EASA EAD 2012-0207-E. EAD 2012-0217-E retains some 

of the requirements of EAD 2012-207-E, changes the airspeed limitation from TAS to IAS, and 

requires inserting a temporary engine health check procedure into the RFM. We are not issuing this 

superseding AD to adopt the revised EASA requirements, because the airspeed limitations in EAD 

2012-21-51 currently use IAS, and the revised engine health check procedure does not correct the 

unsafe condition. 

 In addition, we have been informed by EASA that newly-designed T/R blades with a P/N not 

listed in EAD 2012-21-51 have been developed and may be installed on these model helicopters, but 

will also be affected by the unsafe condition. Additionally, the compliance interval for the bearing 

removal and inspection required in EAD 2012-21-51 did not allow an operator to perform the 

inspection prior to the last flight of the day, if desired, and would have required the bearing removal 

and inspection after the last flight of the day following any bearing replacement, which was not 

intended when we issued the EAD. Therefore, we are issuing this AD to remove the laminated halfbearing and T/R blade P/Ns from the applicability and revise the language of the removal and 

inspection paragraph to clarify when that inspection is required. 

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 the same type design. 

Related Service Information 

 We reviewed Eurocopter Emergency Alert Service Bulletin (EASB) with two numbers, No. 

01.00.65 for the Model AS350B3 helicopters and No. 01.00.24 for the non-FAA type certificated 

Model AS550C3 helicopters, both Revision 0, and both dated October 4, 2012. The EASB specifies 

installing two placards on the instrument panel and revising the RFM to limit airspeed to both 100 

knots IAS and TAS, on-aircraft checking of the bearings after each flight, and performing a one-time 

removal and inspection of the bearings. The EASB also defines an RFM procedure in case of in-flight 

vibrations originating in the tail rotor. Revision 1 of the EASB, dated October 18, 2012, which 

AD To Be Superseded
6 

Eurocopter issued after we issued EAD 2012-21-51, introduced a new procedure for the periodic 

‘‘Engine Health Check'' procedure, and specified to remove the placard and RFM changes with the 

VNE TAS limitation. Revision 2 of the EASB, dated November 2, 2012, accounted for newly 

designed T/R blades by removing specific part-numbered T/R blades from the Effectivity section of 

the EASB. 

AD Requirements 

 This AD retains the requirements of EAD 2012-21-51, expands the applicability by removing the 

half-bearing and the T/R blade P/Ns from the applicability paragraph, clarifies that the removal and 

inspection of the bearings is not a daily inspection, and clarifies that the inspection of the bearings 

may be performed prior to the last flight of the day (not after the last flight of the day). 

Differences Between This AD and the EASA AD 

 The EASA AD requires removing the placard and RFM changes with the TAS limitation and 

replacing it with an IAS limitation. Since the FAA EAD did not include the TAS limitation, this AD 

does not need to require removing it. This AD does not require inserting the temporary engine health 

check procedure in the RFM. 

Interim Action 

 We consider this AD interim action. The design approval holder is currently developing a 

modification that will address the unsafe condition specified in this AD. Once this modification is 

developed, approved, and available, we might consider additional rulemaking. 

Costs of Compliance 

 We estimate that this AD will affect 18 helicopters of U.S. Registry. 

 We estimate that operators may incur the following costs in order to comply with this AD. 

Installing a placard and revising the RFM will require about .5 work-hour, at an average labor rate of 

$85 per hour, for a cost per helicopter of $43 and a total cost to U.S. operators of $774. 

Disassembling and inspecting the bearings will require about 6 work-hours, at an average labor rate 

of $85 per hour, for a cost per helicopter of $510 and a total cost to U.S. operators of $9,180. 

 If necessary, replacing the bearings installed on the aircraft will require about 6 work-hours, at 

an average labor rate of $85, and required parts will cost $2,415, for a cost per helicopter of $2,925. 

FAA's Justification and Determination of the Effective Date 

 The short compliance time involved is required because the previously described unsafe 

condition can adversely affect both the structural integrity and controllability of the helicopter. 

Therefore, because several of the corrective actions are required before further flight, this AD must 

be issued immediately. 

 Since an unsafe condition exists that requires the immediate adoption of this AD, we determined 

that notice and opportunity for public comment before issuing this AD are impracticable and that 

good cause exists for making this amendment effective in less than 30 days. 

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. 

AD To Be Superseded
7 

 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 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, 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): 

AD To Be Superseded
8 

FAA 

Aviation Safety

AIRWORTHINESS DIRECTIVE

www.faa.gov/aircraft/safety/alerts/ 

www.gpoaccess.gov/fr/advanced.html

CORRECTION: Federal Register Volume 78, Number 156 (Tuesday, August 13, 2013); Pages 

49115-49116. 

2012-25-04 Eurocopter France: Amendment 39-17285; Docket No. FAA-2012-1297; Directorate 

Identifier 2012-SW-100-AD. 

(a) Applicability 

 This AD applies to Eurocopter France (Eurocopter) Model AS350B3 helicopters with 

Modification (MOD) 07 5601 installed, certificated in any category. 

 Note 1 to paragraph (a): MOD 07 5601 is an integral part of a specific Model AS350B3 

configuration, commercially identified as ‘‘AS350B3e'' and is not fitted on Model AS350B3 

helicopters of other configurations. 

(b) Unsafe Condition 

 This AD defines the unsafe condition as severe vibrations due to failure of laminated halfbearings (bearings). This condition could result in failure of the tail rotor and subsequent loss of 

control of the helicopter. 

(c) Affected ADs 

 This AD supersedes Emergency AD No. 2012-21-51, Directorate Identifier 2012-SW-095-AD, 

dated October 17, 2012. 

(d) Effective Date 

 This AD becomes effective May 9, 2013. 

(e) 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. 

(f) Required Actions 

 (1) Before further flight: 

 (i) Install a velocity never exceed (VNE) placard that reads as follows on the instrument panel in 

full view of the pilot and co-pilot with 6-millimeter red letters on a white background: 

 VNE LIMITED TO 100 KTS IAS. 

 (ii) Replace the IAS limit versus the flight altitude placard located inside the cabin on the center 

post with the placard as depicted in Table 1 to paragraph (f) of this AD: 

AD To Be Superseded
9 

Table 1 to Paragraph (f) 

VNE POWER ON 

Hp (ft) IAS (kts) 

0 100 

2000 97 

4000 94 

6000 91 

8000 88 

10000 85 

12000 82 

14000 79 

16000 76 

18000 73 

20000 70 

22000 67 

Valid for VNE POWER OFF 

 (2) Before further flight, revise the Rotorcraft Flight Manual (RFM) by inserting a copy of this 

AD into the RFM or by making pen and ink changes as follows: 

 (i) Revise paragraph 2.3 of the RFM by inserting the following: 

 VNE limited to 100 kts IAS. 

 (ii) Revise paragraph 2.6 of the RFM by inserting Table 2 to Paragraph (f) of this AD. 

AD To Be Superseded
10 

Table 2 to Paragraph (f) 

VNE POWER ON 

Hp (ft) IAS (kts) 

0 100 

2000 97 

4000 94 

6000 91 

8000 88 

10000 85 

12000 82 

14000 79 

16000 76 

18000 73 

20000 70 

22000 67 

Valid for VNE POWER OFF 

 (iii) Add the following as paragraph 3.3.3 to the RFM: 

3.3.3 IN-FLIGHT VIBRATIONS FELT IN THE PEDALS 

 Symptom: 

IN-FLIGHT VIBRATIONS FELT IN THE PEDALS 

 1. CHECK PEDAL EFFECTIVENESS 

 2. SMOOTHLY REDUCE THE SPEED TO VY 

 3. AVOID SIDESLIP AS MUCH AS POSSIBLE 

LAND AS SOON AS POSSIBLE 

 (3) Before further flight, and thereafter after each flight, without exceeding 3 hours time-inservice between two checks, visually check each bearing as follows: 

 (i) Position both tail rotor blades horizontally. 

 (ii) Apply load (F) by hand, perpendicular to the pressure face of one tail rotor blade (a), as 

shown in Figure 1 to paragraph (f) of this AD, taking care not to reach the extreme position against 

the tail rotor hub. The load will deflect the tail rotor blade towards the tail boom. 

 (iii) While maintaining the load, check all the visible faces of the bearings (front and side faces) 

in area B of DETAIL A of Figure 1 to paragraph (f) of this AD for separation between the elastomer 

and metal parts, a crack in the elastomer, or an extrusion (see example in Figure 2 to paragraph (f) of 

this AD). A flashlight may be used to enhance the check. 

AD To Be Superseded
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AD To Be Superseded
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 (iv) Repeat paragraphs (f)(3)(i) through (f)(3)(iii) on the other tail rotor blade. 

 (v) Apply load (G) by hand perpendicular to the suction face of one tail rotor blade as shown in 

Figure 3 to paragraph (f) of this AD. The load will deflect the tail rotor blade away from the tail 

boom. 

AD To Be Superseded
13 

 (vi) While maintaining the load, check visible faces of Area C as shown in Figure 3 to paragraph 

(f) of this AD for any extrusion. A flashlight may be used to enhance the check. 

 (vii) Repeat paragraphs (f)(3)(v) and (f)(3)(vi) on the other tail rotor blade. 

 (4) The actions required by paragraphs (f)(3)(i) through (f)(3)(vii) of this AD may be performed 

by the owner/operator (pilot) holding at least a private pilot certificate, and must be entered into the 

aircraft records showing compliance with this AD in accordance with 14 CFR 43.9 (a)(1)-(4) and 14 

CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 

135.439. 

 (5) If there is an extrusion on any bearing, before further flight, replace the four bearings with 

airworthy bearings. 

 (6) If there is a separation or a crack on the pressure side bearing, measure the separation or the 

crack. If the separation or crack is greater than 5 millimeters (.196 inches) as indicated by dimension 

‘‘L'' in Figure 4 to paragraph (f), before further flight, replace the four bearings with airworthy 

bearings. 

AD To Be Superseded
14 

 (7) No later than after the last flight of the day, perform a one-time inspection by removing the 

bearings and inspecting for a separation, a crack, or an extrusion. This inspection is not a daily 

inspection. If there is a separation, crack, or extrusion, before further flight, replace the four bearings 

with airworthy bearings. 

(g) Special Flight Permits 

 Special flight permits are prohibited by this AD. 

(h) 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 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. 

 (3) AMOCs approved previously in accordance with Emergency Airworthiness Directive No. 

2012-21-51, dated October 17, 2012, are approved as AMOCs for the corresponding requirements in 

paragraph (f)(7) of this AD. 

(i) Additional Information 

 (1) Eurocopter Emergency Alert Service Bulletin (EASB) No. 01.00.65, Revision 2, dated 

November 2, 2012, which is not incorporated by reference, contains 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 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 European Aviation Safety Agency Emergency AD No. 

2012-0217-E, dated October 19, 2012.

AD To Be Superseded
15 

(j) Subject 

 Joint Aircraft Service Component (JASC) Code: 6400: Tail Rotor. 

 Issued in Fort Worth, Texas, on April 11, 2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

AD To Be Superseded