Federal Register / Vol. 81, No. 88 / Friday, May 6, 2016 / Rules and Regulations 27303 

Accomplishment Instructions of Boeing Alert 

Service Bulletin B787–81205–SB500009–00, 

Issue 001, dated November 16, 2015. 

(i) 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 (j) 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, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (i)(4)(i) and (i)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(j) Related Information 

For more information about this AD, 

contact Caspar Wang, Aerospace Engineer, 

Cabin Safety and Environmental Systems 

Branch, ANM–150S, FAA, Seattle Aircraft 

Certification Office (ACO), 1601 Lind Avenue 

SW., Renton, WA 98057–3356; phone: 425– 

917–6414; fax: 425–917–6590; email: 

caspar.wang@faa.gov. 

(k) 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 B787– 

81205–SB500009–00, Issue 001, dated 

November 16, 2015. 

(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 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. 

(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 April 25, 

2016. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–10404 Filed 5–5–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3741; Directorate 

Identifier 2014–SW–040–AD; Amendment 

39–18507; AD 2016–09–09] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Type Certificate 

Previously Held by Eurocopter France) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2013–08– 

17 for Airbus Helicopters Model SA– 

365N, SA–365N1, AS–365N2, AS 365 

N3, and SA–366G1 helicopters. AD 

2013–08–17 required initial and 

recurring inspections of the 9-degree 

fuselage frame for a crack and repairing 

the frame if a crack exists. This new AD 

modifies the compliance times and 

expands the inspection area of the 

9-inch frame. The actions of this AD are 

intended to detect a crack in the 

9-degree frame to prevent loss of 

structural integrity and subsequent loss 

of control of the helicopter. 

DATES: This AD is effective June 10, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of June 10, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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, 

10101 Hillwood Pkwy., Room 6N–321, 

Fort Worth, TX 76177. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3741. 

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–2015– 

3741; 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 European Aviation 

Safety Agency (EASA) AD, any 

incorporated-by-reference 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, 10101 

Hillwood Pkwy., Fort Worth, Texas 

76177; telephone (817) 222–5110; email 

robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to remove AD 2013–08–17, 

Amendment 39–17434 (78 FR 25380, 

May 1, 2013) and add a new AD. AD 

2013–08–17 applied to Airbus 

Helicopters Model SA–365N, SA– 

365N1, AS–365N2, AS 365 N3, and SA– 

366G1 helicopters and required initial 

and recurring inspections of the inner 

angles and flanges of the 9-degree 

fuselage frame on the right-hand (RH) 

and left-hand (LH) sides for a crack. If 

a crack was found, AD 2013–08–17 

required repairing the frame. AD 2013– 

08–17 was prompted by EASA 

Emergency AD No. 2010–0064–E, dated 

April 1, 2010, to correct an unsafe 

condition for the specified model 


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27304 Federal Register / Vol. 81, No. 88 / Friday, May 6, 2016 / Rules and Regulations 

helicopters. EASA, which is the 

Technical Agent for the Member States 

of the European Union, advises that of 

a crack found in the 9-degree frame of 

an AS 365 N2 helicopter that had logged 

a total of 10,786 flight hours. EASA 

states that the time required for 

initiation of a crack in this area varies 

according to the weight and balance 

data of the different aircraft versions. 

The NPRM published in the Federal 

Register on December 21, 2015 (80 FR 

79274). The NPRM was prompted by 

EASA AD No. 2014–0159, dated July 7, 

2014, which supersedes EASA 

Emergency AD No. 2010–0064–E. EASA 

advises of further analysis on the 

strength of the 9-degree frame by Airbus 

Helicopters, which indicates 

compliance times should be modified 

and the inspection area expanded. 

Consequently, the NPRM proposed 

retaining the inspections of the 9-degree 

fuselage frame for a crack but in the 

expanded area and within the modified 

compliance times. These actions are 

intended to detect a crack in the 

9-degree frame to prevent loss of 

structural integrity and subsequent loss 

of control of the helicopter. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(80 FR 79274, December 21, 2015). 

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 

We do not require contacting the 

manufacturer for approved repair 

instructions. We also do not allow flight 

with a known crack. 

Related Service Information Under 1 

CFR Part 51 

Airbus Helicopters has issued an 

Emergency Alert Service Bulletin 

(EASB), Revision 2, dated April 7, 2014, 

containing the following three numbers: 

No. 05.00.57 for the Model SA–365N 

and N1, and AS–365N2 and N3 and for 

military Model AS365F, Fs, Fi, and K 

helicopters; No. 05.39 for Model SA– 

366G1 and military Model SA 366–GA 

helicopters; and No. 05.00.25 for 

military Model AS565MA, MB, SA, SB, 

and UB helicopters. 

The EASB specifies checking at 

regular intervals for a crack in the areas 

of the inner angles and flanges of the 9- 

degree frame on the RH and LH sides, 

near the splice. Revision 2 of the EASB 

modifies the compliance times, adds a 

compliance time based on take-off/

landing cycles, and expands the 

inspection areas up to the junction with 

the upper part of the frame. EASA 

classified this service information as 

mandatory and issued EASA AD No. 

2014–0159 to ensure the continued 

airworthiness of these helicopters. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 40 

helicopters of U.S. Registry and that 

labor costs average $85 a work hour. 

Based on these estimates, we expect the 

following costs: 

• Inspecting the 9-degree frame 

requires 3 work-hours per inspection for 

a cost of $255 per helicopter and 

$10,200 for the fleet per inspection 

cycle. 

• Repairing the 9-degree frame 

requires 24 work-hours for a labor cost 

of $2,040. Parts cost $3,350 for a total 

cost of $5,390 per helicopter. 

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 

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 

removing Airworthiness Directive (AD) 

2013–08–17, Amendment 39-17434 (78 

FR 25380, May 1, 2013) and adding the 

following new AD: 

2016–09–09 Airbus Helicopters (Previously 

Eurocopter France): Amendment 39– 

18507; Docket No. FAA–2015–3741; 

Directorate Identifier 2014–SW–040–AD. 

(a) Applicability 

This AD applies to Airbus Helicopters 

Model SA–365N, SA–365N1, AS–365N2, AS 

365 N3, and SA–366G1 helicopters, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the 9-degree frame, which could 

result in the loss of structural integrity and 

subsequent loss of control of the helicopter. 


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Federal Register / Vol. 81, No. 88 / Friday, May 6, 2016 / Rules and Regulations 27305 

(c) Affected ADs 

This AD supersedes AD 2013–08–17, 

Amendment 39–17434 (78 FR 25380, May 1, 

2013). 

(d) Effective Date 

This AD becomes effective June 10, 2016. 

(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) Within 110 hours time-in-service (TIS) 

after reaching the hours or landings 

threshold, whichever occurs first, listed in 

Table 1 to Paragraph (f)(1) of this AD or 

within 110 hours TIS from the effective date 

of this AD, whichever occurs later, and 

thereafter at intervals not to exceed 110 hours 

TIS, using a 10X or higher magnifying glass 

and a light, inspect the 9-degree fuselage 

frame on the right-hand and left-hand sides 

for a crack in the areas depicted in Figures 

1 and 2 of Airbus Helicopters Emergency 

Alert Service Bulletin (EASB) No. AS365 

05.00.57, Revision 2, dated April 7, 2014, or 

EASB No. SA366 05.39, Revision 2, dated 

April 7, 2014, as applicable to your model 

helicopter. For purposes of this AD, a landing 

would be counted anytime the helicopter lifts 

off into the air and then lands again 

regardless of the duration of the landing and 

regardless of whether the engine is shut 

down. 

TABLE 1 TO PARAGRAPH (f)(1) 

Helicopter model Hours 

TIS Landings 

SA–365N .................. 11,490 22,980 

SA–365N1 ................ 10,490 20,980 

AS–365N2 ................ 9,140 18,280 

AS–365N3 ................ 8,740 17,480 

SA–366G1 ................ 8,390 16,780 

(2) If there is a crack, before further flight, 

repair the frame. Repairing a frame does not 

constitute terminating actions for the 

repetitive inspection requirements of this 

AD. 

(g) 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, 10101 Hillwood Pkwy., Fort 

Worth, Texas 76177; telephone (817) 222– 

5110; email 9-ASW-FTW-AMOC-Requests@

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. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2014–0159, dated July 7, 2014. You may 

view the EASA AD on the Internet at 

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

FAA–2015–3741. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5311, Fuselage Main, Frame. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) Airbus Helicopters Emergency Alert 

Service Bulletin No. 05.00.57, Revision 2, 

dated April 7, 2014. 

(ii) Airbus Helicopters Emergency Alert 

Service Bulletin No. 05.39, Revision 2, dated 

April 7, 2014. 

Note 1 to paragraph (j)(2): Airbus 

Helicopters Emergency Alert Service Bulletin 

No. 05.00.57 and Airbus Helicopters 

Emergency Alert Service Bulletin No. 05.39, 

both Revision 2, and both dated April 7, 

2014, are co-published as one document 

along with Airbus Helicopters Emergency 

Alert Service Bulletin No. 05.00.25, Revision 

2, dated April 7, 2014, which is not 

incorporated by reference in this AD. 

(3) For Airbus Helicopters service 

information identified in this final rule, 

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, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. 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 April 22, 

2016. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–10286 Filed 5–5–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8427; Directorate 

Identifier 2014–NM–212–AD; Amendment 

39–18508; AD 2016–09–10] 

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) 2007–10– 

10 R1 for all Airbus Model A300 B4–

600, B4–600R, and F4–600R series 

airplanes, and Model A300 C4–605R 

Variant F airplanes (collectively called 

Model A300–600 series airplanes). AD 

2007–10–10 R1 required revising the 

Airworthiness Limitations Section 

(ALS) of the Instructions for Continued 

Airworthiness to incorporate new 

limitations for fuel tank systems. This 

new AD requires revising the 

maintenance program or inspection 

program to incorporate revised fuel 

maintenance and inspection tasks. This 

AD was prompted by issuance of more 

restrictive maintenance requirements 

and/or airworthiness limitations by the 

manufacturer. We are issuing this AD to 

prevent the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors caused by 

latent failures, alterations, repairs, or 

maintenance actions, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

DATES: This AD becomes effective June 

10, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 10, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of December 28, 2009 (74 FR 

65398, December 10, 2009). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of June 27, 2007 (72 FR 

28827, May 23, 2007). 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus SAS, Airworthiness Office—

EAW, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone 

+33 5 61 93 36 96; fax +33 5 61 93 44 

51; email account.airworth-eas@


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