Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations 17405 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD): 

2008–08–25, Amendment 39–15479 (73 

FR 21240, April 21, 2008), and adding 

the following new AD: 

2014–05–31 The Boeing Company: 

Amendment 39–17803; Docket No. 

FAA–2012–0862; Directorate Identifier 

2011–NM–198–AD. 

(a) Effective Date 

This AD is effective May 2, 2014. 

(b) Affected ADs 

This AD supersedes AD 2008–08–25, 

Amendment 39–15479 (73 FR 21240, April 

21, 2008). 

(c) Applicability 

This AD applies to The Boeing Company 

airplanes, certificated in any category, as 

specified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) Model 747–400F series airplanes, as 

identified in Boeing Alert Service Bulletin 

747–25A3580, Revision 2, dated May 13, 

2013. 

(2) Model 747–400 series airplanes, as 

identified in Boeing Alert Service Bulletin 

747–25A3581, Revision 1, dated June 30, 

2011. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

continued water damage to diode fire card 

285U0072–1 in the M826 automatic fire 

overheat logic test system cardfile following 

a false FWD CARGO FIRE message, with no 

change in frequency, which resulted in an air 

turn back. We are issuing this AD to prevent 

water from exiting over the edge of the 

existing drip shield and contaminating 

electrical components in the M826 cardfile, 

which could result in an electrical short and 

potential loss of several functions essential 

for safe flight. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Installation and Replacement 

Within 24 months after the effective date 

of this AD, install aft and forward drain 

tubes, relocate wire bundle routing, install a 

new drip shield and drip shield deflectors, 

and replace insulation blankets, in 

accordance with the Accomplishment 

Instructions of the service information 

identified in paragraph (g)(1), (g)(2), or (g)(3); 

as applicable; of this AD. 

(1) (For Model 747–400F series airplanes) 

Boeing Alert Service Bulletin 747–25A3580, 

Revision 2, dated May 13, 2013. 

(2) (For Model 747–400 series airplanes) 

Boeing Alert Service Bulletin 747–25A3581, 

Revision 1, dated June 30, 2011. 

(3) (For Model 747–400 series airplanes) 

Boeing Alert Service Bulletin 747–25A3581, 

Revision 2, dated September 11, 2012 (for 

Model 747–400 series airplanes). 

(h) Concurrent Actions 

For Group 1 airplanes as identified in 

Boeing Alert Service Bulletin 747–25A3581, 

Revision 1, dated June 30, 2011: Prior to or 

concurrently with the actions required by 

paragraph (g) of this AD, seal the drain slot, 

install spuds, and install left- and right-side 

drain tubes, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–25A3526, Revision 1, 

dated February 20, 2009 (for Model 747–400 

series airplanes), except as specified in 

paragraphs (h)(1) and (h)(2) of this AD. 

(1) Steps 1 through 5 of Figure 2 of Boeing 

Alert Service Bulletin 747–25A3526, 

Revision 1, dated February 20, 2009, are not 

required if work is being accomplished 

concurrently with the actions specified in 

Boeing Alert Service Bulletin 747–25A3581, 

Revision 1, dated June 30, 2011 (for Model 

747–400 series airplanes). 

(2) The portion of ‘‘More Data’’ in step 8 

of Figure 3 of Boeing Alert Service Bulletin 

747–25A3526, Revision 1, dated February 20, 

2009, which says ‘‘Attach drain tube and 

strap above bead on the spud,’’ is not 

required. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 747–25A3580, Revision 1, 

dated July 14, 2011, which is not 

incorporated by reference in this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 (k)(1) 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. 

(k) Related Information 

(1) For more information about this AD, 

contact Francis Smith, Aerospace Engineer, 

Cabin Safety & Environmental Control 

Systems, ANM–150S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue SW., 

Renton, Washington 98057–3356; phone: 

425–917–6596; fax: 425–917–6590; email: 

francis.smith@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD may be obtained at the addresses 

specified in paragraphs (l)(3) and (l)(4) of this 

AD. 

(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) Boeing Alert Service Bulletin 747– 

25A3526, Revision 1, dated February 20, 

2009. 

(ii) Boeing Alert Service Bulletin 747– 

25A3580, Revision 2, dated May 13, 2013. 

(iii) Boeing Alert Service Bulletin 747– 

25A3581, Revision 1, dated June 30, 2011. 

(iv) Boeing Alert Service Bulletin 747– 

25A3581, Revision 2, dated September 11, 

2012. 

(3) For Boeing 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 98057–3356. 

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 March 5, 

2014. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–05558 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–2013–0701; Directorate 

Identifier 2013–NM–073–AD; Amendment 

39–17768; AD 2014–04–09] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 727 airplanes. 

This AD will complete certain 

mandated programs intended to support 

the airplane reaching its limit of validity 


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17406 Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations 

(LOV) of the engineering data that 

support the established structural 

maintenance program. This AD requires 

repetitive inspections for cracking of 

small repairs done on the vertical flange 

of the rib chord, repetitive inspections 

for cracking along the upper fillet radius 

of the rib chord, and a large repair or 

preventive modification if necessary. 

Accomplishment of a large repair or 

preventive modification terminates the 

actions of this AD. We are issuing this 

AD to prevent cracks in the rib upper 

chord, which could result in the 

inability of the wing structure to 

support the limit load condition, and 

consequent loss of structural integrity of 

the wing. 

DATES: This AD is effective May 2, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 2, 2014. 

ADDRESSES: 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. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2013– 

0701; 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 

Docket 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: 

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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all The Boeing Company Model 

727 airplanes. The NPRM published in 

the Federal Register on August 27, 2013 

(78 FR 52875). The NPRM proposed to 

require repetitive inspections for 

cracking of small repairs done on the 

vertical flange of the rib chord, 

repetitive inspections for cracking along 

the upper fillet radius of the rib chord, 

and a large repair or preventive 

modification if necessary. 

Accomplishment of a large repair or 

preventive modification would 

terminate the actions of the NPRM. We 

are issuing this AD to prevent cracks in 

the rib upper chord, which could result 

in the inability of the wing structure to 

support the limit load condition, and 

consequent loss of structural integrity of 

the wing. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 52875, 

August 27, 2013) and the FAA’s 

response to each comment. 

Request To Remove Statement of 

Difference Between NPRM (78 FR 

52875, August 27, 2013) and Service 

Information 

Boeing requested that we revise 

‘‘Differences Between the Proposed AD 

and the Service Information’’ in the 

NPRM (78 FR 52875, August 27, 2013) 

to instead state that there are no 

differences. Boeing stated that the 

NPRM specified the same type, location, 

and interval of the inspections specified 

in Boeing Service Bulletin 727–57– 

0112, Revision 5, dated July 31, 1997, 

for a small repair. 

We find that clarification of the 

requirements of this final rule is 

necessary in light of the information 

provided in Boeing Service Bulletin 

727–57–0112, Revision 5, dated July 31, 

1997. The post-small-repair inspection 

is described in Part III of the service 

information; some of this information is 

provided in notes, and the description 

of the area to be inspected needed slight 

clarification. To ensure that operators 

understand that all actions specified in 

Part III are required for compliance, and 

to give more specific direction to the 

area of inspection, paragraph (g) in this 

final rule specifies these actions, 

including the information in the notes, 

with slightly different wording to 

describe the inspection area. Since the 

inspection is a direct requirement of this 

final rule, there is a difference between 

this AD and the service information. We 

have not changed this final rule 

regarding this issue. 

Request To Refer to a Single Service 

Information Source 

Paragraph (g) of the NPRM (78 FR 

52875, August 27, 2013) referred to 

actions specified in ‘‘Boeing 727 Service 

Bulletin 57–112; or Part III of the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–57–0112.’’ Boeing 

stated that only one of these references 

is required. Boeing added that one of the 

references did not follow the standard 

format. Boeing therefore requested that 

we revise the NPRM to refer to only 

‘‘Part III of the Accomplishment 

Instructions of Boeing Service Bulletin 

727–57–0112.’’ 

We disagree to revise the source of 

service information as cited in this final 

rule. We are required by OFR 

regulations to precisely specify all 

possible revisions of this service 

bulletin by their unique identities. 

Boeing Service Bulletin 727–57–0112 

has actually been revised five times; 

some versions are old and were 

published in Boeing’s older service 

bulletin format. The earlier version 

(‘‘Boeing 727 Service Bulletin 57–112’’) 

does not have a separate 

‘‘Accomplishment Instructions’’ section. 

Two citations are therefore necessary to 

refer to the description of the small 

repair actions in the service 

information. However, we have added 

Note 1 to paragraph (g) of this final rule 

to clarify the use of the different 

document citations. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the change described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

52875, August 27, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 52875, 

August 27, 2013). 

Costs of Compliance 

We estimate that this AD affects 106 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 


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Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations 17407 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Inspections (per wing) ... 6 work-hours × $85 per 

hour = $510 per inspection cycle.

$0 $510 per inspection 

cycle.

Up to $108,120 per inspection cycle per airplane. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Large repair 1 2 ................................. 300 work-hours × $85 per hour = $25,500 ............................................... $12,139 $37,639 

Preventive modification 1 3 ............... 57 work-hours × $85 per hour = $4,845 ................................................... 10,614 15,459 

1 Cost for on-condition actions (either 2 or 3), per wing. 2 Cost for large repair, per wing. 

3 Cost for preventive modification, per wing. 

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 

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 adding 

the following new airworthiness 

directive (AD): 

2014–04–09 The Boeing Company: 

Amendment 39–17768; Docket No. 

FAA–2013–0701; Directorate Identifier 

2013–NM–073–AD. 

(a) Effective Date 

This AD is effective May 2, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 727, 727C, 727–100, 727– 

100C, 727–200, and 727–200F series 

airplanes, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD will complete certain mandated 

programs intended to support the airplane 

reaching its limit of validity (LOV) of the 

engineering data that support the established 

structural maintenance program. We are 

issuing this AD to prevent cracks in the rib 

upper chord, which could result in the 

inability of the wing structure to support the 

limit load condition, and consequent loss of 

structural integrity of the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Post-Repair Inspection 

For any small repair that has been done as 

specified in Boeing 727 Service Bulletin 57– 

112; or Part III of the Accomplishment 

Instructions of Boeing Service Bulletin 727– 

57–0112: Within 3,500 flight cycles after the 

small repair was installed or inspected as 

specified in Boeing Service Bulletin 727–57– 

0112, or within 18 months after the effective 

date of this AD, whichever occurs latest, do 

a high frequency eddy current inspection for 

cracking of the vertical flange of the rib chord 

from the inboard side, and do a detailed 

(close visual) inspection for cracking along 

the upper fillet radius of the rib chord, in 

accordance with Part III of the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–57–0112, Revision 5, 

dated July 31, 1997. Repeat the inspections 

thereafter at intervals not to exceed 3,500 

flight cycles until accomplishment of the 

repair or modification specified in paragraph 

(i) or (j) of this AD. 

Note 1 to paragraph (g) of this AD: Boeing 

727 Service Bulletin 57–112 and Boeing 

Service Bulletin 727–57–0112 are both 

versions of the same document. The 

formatting of service bulletins was revised by 

Boeing following publication of Boeing 727 

Service Bulletin 57–112, Revision 1, dated 

April 23, 1976. Boeing Service Bulletin 727– 

57–0112, Revision 2, dated May 19, 1988, 

was published using Boeing’s revised 

formatting. 

(h) Inspection Definition 

For the purposes of this AD, a detailed 

inspection is an intensive examination of a 

specific item, installation, or assembly to 

detect damage, failure, or irregularity. 

Available lighting is normally supplemented 

with a direct source of good lighting at an 


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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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