17408 Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations 

intensity deemed appropriate. Inspection 

aids such as mirror, magnifying lenses, etc., 

may be necessary. Surface cleaning and 

elaborate procedures may be required. 

(i) Corrective Action for Cracks 

If any crack is found during any inspection 

required by paragraph (g) of this AD, before 

further flight, do either action specified in 

paragraph (i)(1) or (i)(2) of this AD. 

Accomplishment of either action terminates 

the requirements of paragraph (g) of this AD. 

(1) Do a large repair, in accordance with 

Part IV of the Accomplishment Instructions 

of Boeing Service Bulletin 727–57–0112, 

Revision 5, dated July 31, 1997. 

(2) Do a preventive modification, in 

accordance with Part V of the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–57–0112, Revision 5, 

dated July 31, 1997. 

(j) Optional Terminating Action 

Accomplishment of the actions specified in 

either paragraph (j)(1) or (j)(2) of this AD 

terminates the requirements of paragraphs (g) 

and (i) of this AD. 

(1) A large repair, in accordance with Part 

IV of the Accomplishment Instructions of 

Boeing Service Bulletin 727–57–0112, 

Revision 5, dated July 31, 1997. Any crack 

found must be repaired before further flight 

using a method approved in accordance with 

the procedures specified in paragraph (l) of 

this AD. 

(2) A preventive modification, in 

accordance with Part V of the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–57–0112, Revision 5, 

dated July 31, 1997. Any crack found must 

be repaired before further flight using a 

method approved in accordance with the 

procedures specified in paragraph (l) of this 

AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

inspections, large repair, and modification 

specified in this AD, if those actions were 

performed before the effective date of this AD 

using Boeing Service Bulletin 727–57–0112, 

Revision 4, dated October 29, 1992. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), 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 

paragraph (m) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(m) Related Information 

For more information about this AD, 

contact Chandraduth Ramdoss, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles Aircraft Certification 

Office (ACO), 3960 Paramount Blvd., Suite 

100, Lakewood, CA 90712–4137, phone: 562– 

627–5329; fax: 562–627–5210; email: 

Chandraduth.Ramdoss@faa.gov. 

(n) 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) Boeing Service Bulletin 727–57–0112, 

Revision 5, dated July 31, 1997. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at 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. 

(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 Renton, Washington, on February 

14, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–06776 Filed 3–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0822; Directorate 

Identifier 2013–SW–004–AD; Amendment 

39–17783; AD 2014–05–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Type Certificate 

Previously Held by Eurocopter France) 

(Airbus Helicopters) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2012–25– 

04 for Eurocopter France Model 

AS350B3 helicopters with a certain 

modification (MOD) installed. AD 2012– 

25–04 required installing two placards 

and revising the Rotorcraft Flight 

Manual (RFM). AD 2012–25–04 also 

required certain checks and inspecting 

and replacing, if necessary, all four 

laminated half-bearings (bearings). This 

new AD retains the previous AD 

requirements, requires certain 

modifications which would be 

terminating action for the airspeed 

limitations, and adds certain helicopter 

models to the bearing inspection with a 

different inspection interval. These 

actions are intended to prevent 

vibration due to a failed bearing, failure 

of the tail rotor, and subsequent loss of 

control of the helicopter. 

DATES: This AD is effective May 2, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of May 2, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax 

(972) 641–3775; or at http://

www.airbushelicopters.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 in Docket No. 

FAA–2013–0822 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 foreign 


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

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, 

Safety Management Group, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On September 23, 2013, at 78 FR 

58256, the Federal Register published 

our notice of proposed rulemaking 

(NPRM), which proposed to amend 14 

CFR part 39 by removing AD 2012–25– 

04, Amendment 39–17285 (78 FR 

24041, April 24, 2013) and adding an 

AD that would apply to Eurocopter 

France (now Airbus Helicopters) Model 

AS350B, AS350BA, AS350B1, 

AS350B2, AS350B3 (except AS350B3 

helicopters with modification (MOD) 07 

5606 installed), AS350C, AS350D, 

AS350D1, AS355E, AS355F, AS355F1, 

AS355F2, AS355N, and AS355NP 

helicopters. For Model AS350B3 

helicopters with MOD 07 5601 installed, 

the NPRM proposed to require limiting 

the velocity never exceed speed by 

installing a placard and revising the 

RFM, checking the bearings after each 

flight for separation, a crack, or 

extrusion, performing a one-time 

inspection of the bearings, modifying 

the chin weight support and replacing 

any bearings with more than 5 hours 

time-in-service (TIS), removing the 

additional chin weights and installing 

blanks, modifying the rotating pitchchange spider assembly, installing a 

load compensator, and modifying the 

electrical installation. After modifying 

the helicopter, the NPRM proposed to 

require removing the RFM limitations 

and placards installed previously. For 

Model AS350B, AS350BA, AS350B1, 

AS350B2, AS350C, AS350D, AS350D1, 

AS355E, AS355F, AS355F1, AS355F2, 

AS355N, AS355NP helicopters, and 

Model AS350B3 helicopters that do not 

have MOD 07 5601 installed, the NPRM 

also proposed to require checking the 

bearings after the last flight of each day 

and replacing the bearings if there is an 

extrusion, a crack, or separation. The 

proposed requirements were intended to 

prevent vibration due to a failed 

bearing, failure of the tail rotor, and 

subsequent loss of control of the 

helicopter. 

The NPRM was prompted by 

Emergency AD No. 2012–0257–E, dated 

December 5, 2012 (EAD 2012–0257–E) 

issued by the European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Union. EASA EAD 2012– 

0257–E advises of premature failures of 

bearings on AS350B3 helicopters, and 

states that the criticality of the bearing 

failures should apply to all AS355 and 

AS350 helicopters. As a result, EAD 

2012–0257–E requires repetitive postflight checks of the bearings. 

EASA then superseded EAD 2012– 

0217–E with EASA AD No. 2013–0029, 

dated February 8, 2013 (AD 2013–0029), 

to correct an unsafe condition for 

Eurocopter Model AS 350 B3 

helicopters modified by MOD 07 5601, 

except for helicopters modified by MOD 

07 5606 in production. EASA advises 

that MOD 07 5606 restores the tail rotor 

dynamic load level to that on 

helicopters before installation of MOD 

07 5601 and eliminates the modified 

loading conditions of bearings which 

caused the intensified deterioration and 

reported failures. For these reasons, 

EASA AD 2013–0029 requires 

incorporation of MOD 07 5606 as a 

terminating action. 

Since we issued the NPRM, 

Eurocopter France has changed its name 

to Airbus Helicopters. This AD reflects 

that change and updates the contact 

information to obtain service 

documentation. 

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 58256, September 23, 

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 helicopter of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed, except for the minor change 

previously described and formatting 

changes. These changes are consistent 

with the intent of the proposals in the 

NPRM (78 FR 58256, September 23, 

2013) and will not increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Differences Between This AD and the 

EASA AD 

The EASA AD requires removing the 

placard and RFM changes with the true 

airspeed limitation (TAS) and replacing 

it with an indicated airspeed limitation. 

Since AD 2012–25–04 did not include 

the TAS limitation, this AD does not 

require removing it. 

Related Service Information 

We reviewed Eurocopter Service 

Bulletin (SB) No. AS350–01.00.66, 

Revision 1, dated February 15, 2013 (SB 

AS350–01.00.66), which describes 

procedures for removing the additional 

chin weights installed on the tail rotor, 

installing a load compensator, and 

modifying the electrical system 

installation, to reduce the dynamic 

loads on the tail rotor. Eurocopter refers 

to the procedures in this SB as MOD 07 

5606. SB AS350–01.00.66 only applies 

to helicopters with MOD 07 5601 

installed. 

We reviewed one 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 

(EASB 01.00.65). EASB 01.00.65 is 

Revision 3, dated February 4, 2013. 

EASB 01.00.65 specifies installing a 

placard on the instrument panel and 

revising the RFM to limit airspeed to 

100 knots IAS, revising the RFM to 

include a procedure in case of in-flight 

vibrations originating in the tail rotor 

and an ‘‘engine health check,’’ checking 

the bearings after each flight, and 

performing a one-time inspection of the 

bearings. EASB 01.00.65 does not apply 

to helicopters with MOD 07 5606 

installed. 

We also reviewed one Eurocopter 

EASB with four numbers: No 05.00.71 

for Model AS350B, BA, BB, D, B1, B2, 

B3, and the non-FAA type certificated 

L1 helicopters; No. 05.00.63 for Model 

AS355E, F, F1, F2, N, and NP 

helicopters; No. 05.00.46 for the nonFAA type certificated Model AS550A2, 

C2, C3, and U2 helicopters; and No. 

05.00.42 for the non-FAA type 

certificated Model AS555AF, AN, SN, 

UF, and UN helicopters (EASB 

05.00.71). EASB 05.00.71 is Revision 2, 

dated December 19, 2012. EASB 

05.00.71 specifies procedures for 

checking the bearings for deterioration 

or damage after the last flight of each 

day. EASB 05.00.71 does not apply to 

helicopters with MOD 07 5601 installed. 


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We also reviewed Eurocopter SB No. 

AS350–64.00.11, Revision 0, dated 

December 19, 2012 (SB AS350– 

64.00.11), which describes procedures 

for modifying the tail rotor chin weight 

support to prevent interference with the 

bearings. The manufacturer refers to the 

procedures in this SB as MOD 07 6604. 

SB AS350–64.00.11 only applies to 

helicopters with MOD 07 5601 installed. 

Costs of Compliance 

We estimate that the pilot checks of 

the bearings in this AD will affect 938 

helicopters of U.S. Registry, and that 50 

helicopters will be affected by the 

remaining requirements. The cost for 

the pilot checks is minimal. 

We estimate that operators may incur 

the following costs in order to comply 

with this AD. At an average labor rate 

of $85 per hour, installing a placard and 

revising the RFM requires about .5 

work-hour, for a cost per helicopter of 

$43 and a total cost to U.S. operators of 

$2,150. Disassembling and inspecting 

the bearings requires about 6 workhours, for a cost per helicopter of $510 

and a total cost to U.S. operators of 

$25,500. Modifying the chin weight 

support requires about 8 work-hours, for 

a cost per helicopter of $680, and a total 

cost to U.S. operators of $34,000. 

Removing the additional chin weights 

installed on the tail rotor, modifying the 

rotating pitch-change spider assembly, 

installing a load compensator, and 

modifying the electrical system 

installation requires about 200 workhours, and required parts will cost 

$18,343, for a cost per helicopter of 

$35,343, and a total cost to U.S. 

operators of $1,767,150. 

If necessary, replacing the bearings 

installed on the aircraft requires 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. 

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 have 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 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, 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. 

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 

removing Airworthiness Directive (AD) 

2012–25–04, Amendment 39–17285 (78 

FR 24041, April 24, 2013), and adding 

the following new (AD): 

2014–05–10 Airbus Helicopters (Type 

Certificate Previously Held By 

Eurocopter France): Amendment 39– 

17783; Docket No. FAA–2013–0822; 

Directorate Identifier 2013–SW–004–AD. 

(a) Applicability 

This AD applies to Model AS350B, 

AS350BA, AS350B1, AS350B2, AS350B3 

(except AS350B3 helicopters with 

modification (MOD) 07 5606 installed), 

AS350C, AS350D, AS350D1, AS355E, 

AS355F, AS355F1, AS355F2, AS355N, and 

AS355NP helicopters, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

severe vibrations due to failure of laminated 

half-bearings (bearings). This condition could 

result in failure of the tail rotor and 

subsequent loss of control of the helicopter. 

(c) Affected AD 

This AD supersedes AD No. 2012–25–04, 

Amendment 39–17285 (78 FR 24041, April 

24, 2013). 

(d) Effective Date 

This AD becomes effective May 2, 2014. 

(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 Action 

(1) For Model AS350B3 helicopters with 

MOD 07 5601 installed: 

Note 1 to paragraph (f) of this AD: MOD 

075601 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. 

(i) Before further flight: 

(A) 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. 

(B) Replace the IAS limit versus the flight 

altitude placard located inside the cabin on 

the center post with the placard as depicted 

in Figure 1 to paragraph (f) of this AD: 

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 

Figure 1 to paragraph (f) 

(ii) 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: 

(A) Revise paragraph 2.3 of the RFM by 

inserting the following: 

VNE limited to 100 kts IAS. 

(B) Revise paragraph 2.6 of the RFM by 

inserting Figure 2 to paragraph (f) of this AD. 


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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 

Figure 2 to paragraph (f) 

(C) 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 

(iii) Before further flight, and thereafter 

after each flight, without exceeding 3 hours 

time-in-service (TIS) between two checks, 

visually check each bearing as follows: 

(A) Position both tail rotor blades 

horizontally. 

(B) Apply load (F) by hand, perpendicular 

to the pressure face of one tail rotor blade (a), 

as shown in Figure 3 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. 

(C) While maintaining the load, check all 

the visible faces of the bearings (front and 

side faces) in area B of DETAIL A of Figure 

3 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 4 to paragraph (f) of this 

AD). A flashlight may be used to enhance the 

check. 

BILLING CODE 4910–13–P 


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DETAIL A 

Figure 3 to paragraph (t) 
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Figure 4 to paragraph (f) 
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(D) Repeat paragraphs (f)(1)(iii)(A) through 

(f)(1)(iii)(C) of this AD on the other tail rotor 

blade. 

(E) Apply load (G) by hand perpendicular 

to the suction face of one tail rotor blade as 

shown in Figure 5 to paragraph (f) of this AD. 

The load will deflect the tail rotor blade away 

from the tail boom. 


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II 

Figure 5 to paragraph (f) 
Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations 17415 

(F) While maintaining the load, check 

visible faces of Area C as shown in Figure 5 

to paragraph (f) of this AD for any extrusion. 

A flashlight may be used to enhance the 

check. 

(G) Repeat paragraphs (f)(1)(iii)(E) and 

(f)(1)(iii)(F) of this AD on the other tail rotor 

blade. 

(iv) The actions required by paragraphs 

(f)(1)(iii)(A) through (f)(1)(iii)(G) 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. 

(v) If there is an extrusion on any bearing, 

before further flight, replace the four bearings 

with airworthy bearings. 

(vi) 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 6 to paragraph (f) of this AD, before 

further flight, replace the four bearings with 

airworthy bearings. 

BILLING CODE 4910–13–C 

(vii) 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. 

(viii) Within 130 hours TIS: 

(A) Modify the chin weight support as 

described in the Accomplishment 

Instructions, paragraphs 3.B.2.a through 

3.B.2.h, of Eurocopter Service Bulletin (SB) 

No. AS350–64.00.11, Revision 0, dated 

December 19, 2012. 

(B) Remove the additional chin weights, 

install blanks on the chin weights, replace 

bearings with more than 5 hours TIS, and reidentify the blade assembly as described in 

the Accomplishment Instructions, paragraph 

3.B.2.a., of Eurocopter SB No. AS350– 

01.00.66, Revision 1, dated February 15, 2013 

(SB AS350–01.00.66). 

(C) Modify and re-identify the rotating 

pitch-change spider assembly as described in 

the Accomplishment Instructions, paragraph 

3.B.2.b., of SB AS350–01.00.66. 

(D) Install a load compensator as described 

in the Accomplishment Instructions, 

paragraph 3.B.3.b., of SB AS350–01.00.66. 

(E) Modify the electrical installation as 

described in the Accomplishment 

Instructions, section 3.B.4., of SB AS350– 

01.00.66. 

Note 2 to paragraph (f) of this AD: The 

manufacturer refers to the actions in 

paragraphs (f)(1)(viii)(B) through (f)(1)(viii)(E) 

of this AD as MOD 07 5606. 

(ix) After modification of a helicopter as 

required by paragraphs (f)(1)(viii)(A) through 

(f)(1)(viii)(E) of this AD, the actions of 

paragraph (f)(1)(iii) through (f)(1)(vii) of this 

AD are no longer required and the operating 

limitation placards and RFM procedures 

required by paragraphs (f)(1)(i) through 

(f)(1)(ii)(C) of this AD may be removed. 

(2) For Model AS350B, AS350BA, 

AS350B1, AS350B2, AS350C, AS350D, 

AS350D1, AS355E, AS355F, AS355F1, 

AS355F2, AS355N, AS355NP helicopters, 

and Model AS350B3 helicopters that do not 

have MOD 07 5601 installed: 

(i) No later than after the last flight of the 

day, and thereafter during each last flight of 

the day check, without exceeding 10 hours 

TIS between two checks, visually check each 

bearing as described in paragraphs 

(f)(1)(iii)(A) through (f)(1)(vi) of this AD. 

(ii) If there is an extrusion on any bearing, 

before further flight, replace the bearing with 

an airworthy bearing. 


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17416 Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations 

(iii) If there is a separation or a crack on 

the bearing, measure the separation or the 

crack. If the separation or crack is greater 

than 5 mm (.196 inches) as indicated by 

dimension ‘‘L’’ and greater than 2 mm (.078 

inches) as indicated by dimension ‘‘P’’ in 

Figure 3 of Eurocopter Emergency Alert 

Service Bulletin (EASB) No. 05.00.71 or No. 

05.00.63, both Revision 2 and both dated 

December 19, 2012, as applicable to your 

model helicopter, before further flight, 

replace the bearing. 

(g) Credit for Actions Previously Completed 

Actions accomplished before the effective 

date of this AD in accordance with 

Emergency AD No. 2012–21–51, dated 

October 19, 2012, or AD No. 2012–25–04, 

Amendment 39–17285 (78 FR 24041, April 

24, 2013) are considered acceptable for 

compliance with the corresponding actions 

of this AD. 

(h) Special Flight Permits 

Special flight permits are prohibited. 

(i) 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– 

5328; 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. 

(j) Additional Information 

(1) Eurocopter EASB No. 01.00.65 and No. 

01.00.24, both Revision 3 and both dated 

February 4, 2013, which are co-published as 

one document and which are not 

incorporated by reference, contain additional 

information about the subject of this AD. For 

this service information, contact Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone (972) 

641–0000 or (800) 232–0323; fax (972) 641– 

3775; or at http://

www.airbushelicopters.com/techpub. You 

may review this 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. 

2013–0029, dated February 8, 2013, which 

can be found on the Internet at http://

www.regulations.gov in Docket number 

2013–0822. 

(k) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6400: Tail Rotor. 

(l) 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 Service Bulletin No. AS350– 

64.00.11, Revision 0, dated December 19, 

2012. 

(ii) Eurocopter Service Bulletin No. AS350– 

01.00.66, Revision 1, dated February 15, 

2013. 

(iii) Eurocopter Emergency Alert Service 

Bulletin No. 05.00.71, Revision 2, dated 

December 19, 2012. 

(iv) Eurocopter Emergency Alert Service 

Bulletin No. 05.00.63, Revision 2, dated 

December 19, 2012. 

Note 3 to paragraph (l)(2): Eurocopter 

Emergency Alert Service Bulletin No. 

05.00.71, Revision 2, dated December 19, 

2012, and Eurocopter Emergency Alert 

Service Bulletin No. 05.00.63, Revision 2, 

dated December 19, 2012, are co-published as 

one document along with Eurocopter 

Emergency Alert Service Bulletin No. 

05.00.46, Revision 2, dated December 19, 

2012, and Eurocopter Emergency Alert 

Service Bulletin No. 05.00.42, Revision 2, 

dated December 19, 2012, which are not 

incorporated by reference in this AD. 

(3) For Eurocopter service information 

identified in this AD, contact Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone (972) 

641–0000 or (800) 232–0323; fax (972) 641– 

3775; or at http://

www.airbushelicopters.com/techpub. 

(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 February 

20, 2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–06769 Filed 3–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1253; Directorate 

Identifier 2011–NM–079–AD; Amendment 

39–17723; AD 2013–26–14] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2008–08– 

04 for certain Airbus Model A318, 

A319, A320, and A321 series airplanes. 

AD 2008–08–04 required repetitive 

inspections for cracking in the forward 

lug of the support rib 5 fitting of the left 

and right main landing gear (MLG), and 

repair or replacement of any cracked 

MLG fitting if necessary. AD 2008–08– 

04 also required modification of the rib 

bushings of the left and right MLG, 

which ended the repetitive inspections. 

This new AD requires, for airplanes on 

which certain modifications or repairs 

have been done, repetitive inspections 

for cracks of the forward lug of each lefthand and right-hand MLG support rib 5 

fitting, and repair if necessary; and adds 

Model A318 series airplanes to the 

applicability. Replacement of an MLG 

support rib 5 fitting terminates the 

repetitive inspection requirements for 

the MLG support rib 5 fitting at that 

position. This AD was prompted by 

reports of cracks found in the forward 

lug of the MLG support rib 5 fitting. We 

are issuing this AD to prevent cracking 

in the forward lug of the MLG, which 

could result in failure of the lug and 

consequent collapse of the MLG during 

takeoff or landing. 

DATES: This AD becomes effective May 

2, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 2, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of May 19, 2008 (73 FR 

19975, April 14, 2008). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2011-1253; or in 

person at the U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 


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