9746 Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations 

tachometer boxes identified in paragraph 

(c)(1) of this AD that also have installed 

electrical connectors labeled as P10106, 

P10098, and P10108; or P11F, P13F, and 

P15F. 

(d) Reason 

This AD was prompted by reports of 

uncommanded in-flight shutdowns (IFSDs). 

We are issuing this AD to prevent failure of 

the tachometer box, which could lead to 

failure of the engine, IFSD, and loss of 

control of the helicopter. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Within 1,600 flight hours after the 

effective date of this AD, remove the affected 

tachometer box from the engine. 

(2) Reserved. 

(f) Credit for Previous Action 

You may take credit for the action required 

by paragraph (e) of this AD if you performed 

the action before the effective date of this AD 

in accordance with Turbomeca S.A. 

Mandatory Service Bulletin 292 77 0844, 

Version A, dated March 4, 2015. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. You may email your 

request to: ANE–AD–AMOC@faa.gov. 

(h) Related Information 

(1) For more information about this AD, 

contact Philip Haberlen, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7770; fax: 781–238–7199; email: 

philip.haberlen@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2015–0175, dated August 

24, 2015, which includes Mandatory Service 

Bulletin No. 292 77 0844, Version B, dated 

July 6, 2015, for related information. You 

may examine the MCAI in the AD docket on 

the Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2015–4070. 

(3) Turbomeca S.A. Mandatory Service 

Bulletin No. 292 77 0844, Version B, dated 

July 6, 2015, which is not incorporated by 

reference in this AD, can be obtained from 

Turbomeca S.A., using the contact 

information in paragraph (h)(4) of this AD. 

(4) For service information identified in 

this AD, contact Turbomeca S.A., 40220 

Tarnos, France; phone: 33 (0)5 59 74 40 00; 

fax: 33 (0)5 59 74 45 15. 

(5) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

1200 District Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(i) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

February 16, 2016. 

Ann C. Mollica, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–04028 Filed 2–25–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1280; Directorate 

Identifier 2014–NM–064–AD; Amendment 

39–18404; AD 2016–04–10] 

RIN 2120–AA64 

Airworthiness Directives; ATR—GIE 

Avions de Transport Re ́gional 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

ATR—GIE Avions de Transport 

Re ́gional Model ATR42–500 airplanes, 

and Model ATR72–102, –202, –212, and 

–212A airplanes. This AD was 

prompted by a report of chafed wires 

between electrical harnesses. This AD 

requires inspections for wire 

discrepancies, and corrective actions if 

necessary. We are issuing this AD to 

detect and correct damaged wiring and 

incorrect installation of the wiring 

harness and adjacent air ducts that 

could lead to wire harness chafing and 

arcing, possibly resulting in an on-board 

fire. 

DATES: This AD becomes effective April 

1, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 1, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-1280 or in 

person at the 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. 

For service information identified in 

this final rule, contact ATR—GIE 

Avions de Transport Re ́gional, 1, Alle ́e 

Pierre Nadot, 31712 Blagnac Cedex, 

France; telephone +33 (0) 5 62 21 62 21; 

fax +33 (0) 5 62 21 67 18; email 

continued.airworthiness@atr.fr; Internet 

http://www.aerochain.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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1280. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

fax 425–227–1149. 

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 certain ATR—GIE Avions de 

Transport Re ́gional Model ATR42–500 

airplanes, and Model ATR72–102, –202, 

–212, and –212A airplanes. The NPRM 

published in the Federal Register on 

May 12, 2015 (80 FR 27114) (‘‘the 

NPRM’’). The NPRM was prompted by 

a report of chafed wires between 

electrical harnesses. The NPRM 

proposed to require inspections for wire 

discrepancies, and corrective actions if 

necessary. We are issuing this AD to 

detect and correct damaged wiring and 

incorrect installation of the wiring 

harness and adjacent air ducts, which 

could lead to wire harness chafing and 

arcing, possibly resulting in an on-board 

fire. 

Since the NPRM was issued, the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0171, dated August 20, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for certain ATR— 

GIE Avions de Transport Re ́gional 

Model ATR42–500 airplanes, and Model 

ATR72–102, –202, –212, and –212A 

airplanes. The MCAI states: 

An erroneous cockpit indication has been 

reported on an in-service aeroplane. 

Subsequent investigation identified chafed 

wiring between harnesses (2M–2S–6M) and 

the metallic structure of the cargo lining 

panel above the electronic rack 90VU shelf. 

The chafing was most likely the result of 

incorrect harness installation. In some cases, 

the bracket, which supports the harnesses, 

could be incorrectly positioned. 

Consequently, the wiring harnesses, and in 

certain configurations, the adjacent air duct, 

could be incorrectly routed. 

mstockstill on DSK4VPTVN1PROD with RULES

Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations 9747 

This condition, if not detected and 

corrected, could lead to wiring harness 

chafing and arcing, possibly resulting in an 

on-board fire. 

Prompted by this unsafe condition, EASA 

issued AD 2014–0052 (later revised) [http:// 

www.casa.gov.au/wcmswrs/main/lib100154/

2014–0052.pdf] to require a one-time visual 

inspection of the affected area including a 

bracket position check and, depending on 

findings, accomplishment of applicable 

corrective actions. 

Since EASA AD 2014–0052R1 [http://

ad.easa.europa.eu/blob/easa_ad_2014_0052_

R1_superseded.pdf/AD_2014-0052R1_1] was 

issued, ATR determined that more 

aeroplanes are potentially affected (referred 

as Group B aeroplanes) than originally 

identified. It was also determined that some 

aeroplanes, originally addressed by AD 

2014–0052, are not affected due to their 

specific configuration. Taking into account 

these findings, ATR issued Revision 03 of 

Service Bulletin (SB) ATR42–92–0024 and 

SB ATR72–92–1032 to reflect the reidentified 

population of affected aeroplanes. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2014–0052R1, which is superseded, and 

requires inspection, and, depending on 

findings, applicable corrective action(s), on 

the adjusted range of aeroplanes. 

EASA AD 2015–0171, dated August 

20, 2015, replaces EASA AD 2014– 

0052R1, dated April 7, 2014, which was 

the referenced MCAI in the NPRM. The 

revised MCAI adds certain airplanes 

and removes others from the 

applicability, but does not affect any 

U.S.-registered airplanes. You may 

examine the MCAI in the AD docket on 

the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-1280- 

0003. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Changes to This AD 

Since the NPRM was issued, Avions 

de Transport Re ́gional has issued 

Service Bulletin ATR42–92–0024, 

Revision 03, dated January 21, 2015; 

and Service Bulletin ATR72–92–1032, 

Revision 03, dated January 21, 2015. No 

additional work is required for airplanes 

that have accomplished the actions 

specified in any previous version. We 

have revised paragraphs (g) and (h) of 

this AD to reference this revised service 

information. We have revised paragraph 

(i) of this AD to give credit for actions 

done before the effective date of this AD 

using the following service bulletins. 

• Avions de Transport Re ́gional 

Service Bulletin ATR42–92–0024, 

Revision 01, dated January 16, 2014. 

• Avions de Transport Re ́gional 

Service Bulletin ATR42–92–0024, 

Revision 02, dated April 17, 2014. 

• Avions de Transport Re ́gional 

Service Bulletin ATR72–92–1032, 

Revision 01, dated January 16, 2014. 

• Avions de Transport Re ́gional 

Service Bulletin ATR72–92–1032, 

Revision 02, dated April 17, 2014. 

We have also revised paragraph (c) of 

this AD to refer to the manufacturer 

serial numbers of the affected airplanes 

as identified in EASA AD 2015–0171, 

dated August 20, 2015. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

ATR—GIE Avions de Transport 

Re ́gional has issued the following 

service bulletins. 

• Avions de Transport Re ́gional 

Service Bulletin ATR42–92–0024, 

Revision 03, dated January 21, 2015. 

The service information describes 

procedures for inspecting the electrical 

harness routing on top of the 90VU 

electrical rack, and modification if 

necessary. 

• Avions de Transport Re ́gional 

Service Bulletin ATR72–92–1032, 

Revision 03, dated January 21, 2015. 

The service information describes 

procedures for inspecting the electrical 

harness routing on top of the 90VU 

electrical rack, and modification if 

necessary. 

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 1 

airplane of U.S. registry. 

We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $85, or $85 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 3 work-hours and require parts 

costing $82, for a cost of $337 per 

product. We have no way of 

determining the number of aircraft that 

might need these actions. 

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 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 the 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-1280; 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 

mstockstill on DSK4VPTVN1PROD with RULES

9748 Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations 

information. The street address for the 

Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

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): 

2016–04–10 ATR—GIE Avions de 

Transport Re ́gional: Amendment 39– 

18404. Docket No. FAA–2015–1280; 

Directorate Identifier 2014–NM–064–AD. 

(a) Effective Date 

This AD becomes effective April 1, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the ATR–GIE Avions de 

Transport Re ́gional airplanes identified in 

paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category. 

(1) Model ATR42–500 airplanes, serial 

numbers 443 through 1006 inclusive, and 

1014; except serial numbers 811, 1002, and 

1005. 

(2) Model ATR72–102, –202, –212, and 

–212A airplanes, serial numbers 475 through 

969 inclusive, 971 through 988 inclusive, 

1025, 1028 through 1069 inclusive, 1072, and 

1089 through 1175 inclusive; except serial 

numbers 872, 887, 893, 956, 1042, and 1162. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 92, Electrical Routing. 

(e) Reason 

This AD was prompted by a report of 

chafed wires between electrical harnesses. 

We are issuing this AD to detect and correct 

damaged wiring and incorrect installation of 

the wiring harness and adjacent air ducts that 

could lead to wire harness chafing and 

arcing, possibly resulting in an on-board fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections 

Within 500 flight hours after the effective 

date of this AD, do the actions specified in 

paragraphs (g)(1) and (g)(2) of this AD, in 

accordance with the Accomplishment 

Instructions of Avions de Transport Re ́gional 

Service Bulletin ATR42–92–0024, Revision 

03, dated January 21, 2015; and Avions de 

Transport Re ́gional Service Bulletin ATR72– 

92–1032, Revision 03, dated January 21, 

2015; as applicable. 

(1) Do a general visual inspection for 

damage of the electrical wires of harnesses 

2M–2S–6M. 

(2) Do a general visual inspection for 

correct routing of electrical bundle 2M–2S– 

6M, and correct routing of the air duct. 

(h) Corrective Actions 

(1) If, during the inspection required by 

paragraph (g)(1) of this AD, any damage is 

found on the electrical wires: Before further 

flight, repair the wires, in accordance with 

the Accomplishment Instructions of Avions 

de Transport Re ́gional Service Bulletin 

ATR42–92–0024, Revision 03, dated January 

21, 2015; and Avions de Transport Re ́gional 

Service Bulletin ATR72–92–1032, Revision 

03, dated January 21, 2015; as applicable. 

(2) If, during the inspection required by 

paragraph (g)(2) of this AD, electrical bundle 

2M–2S–6M and/or an air duct is found to be 

incorrectly routed: Within 500 flight hours 

after the effective date of this AD, do a 

general visual inspection for correct 

positioning of the bracket, in accordance 

with the Accomplishment Instructions of 

Avions de Transport Re ́gional Service 

Bulletin ATR42–92–0024, Revision 03, dated 

January 21, 2015; and Avions de Transport 

Re ́gional Service Bulletin ATR72–92–1032, 

Revision 03, dated January 21, 2015; as 

applicable. 

(i) If, during the inspection required by 

paragraph (h)(2) of this AD, the bracket is 

found to be correctly positioned: Within 500 

flight hours after the effective date of this AD, 

do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Avions de Transport Re ́gional 

Service Bulletin ATR42–92–0024, Revision 

03, dated January 21, 2015; and Avions de 

Transport Re ́gional Service Bulletin ATR72– 

92–1032, Revision 03, dated January 21, 

2015; as applicable. 

(ii) If, during the inspection required by 

paragraph (h)(2) of this AD, the bracket is 

found to be missing or incorrectly positioned: 

Within 500 flight hours after the inspection 

required by paragraph (h)(2) of this AD, 

repair using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA); or 

ATR–GIE Avions de Transport Re ́gional’s 

EASA Design Organization Approval (DOA). 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by this AD, if those actions were 

performed before the effective date of this AD 

using the applicable service bulletins 

specified in paragraphs (i)(1) through (i)(6) of 

this AD, which are not incorporated by 

reference in this AD. 

(1) Avions de Transport Re ́gional Service 

Bulletin ATR42–92–0024, dated June 6, 2013. 

(2) Avions de Transport Re ́gional Service 

Bulletin ATR42–92–0024, Revision 01, dated 

January 16, 2014. 

(3) Avions de Transport Re ́gional Service 

Bulletin ATR42–92–0024, Revision 02, dated 

April 17, 2014. 

(4) Avions de Transport Re ́gional Service 

Bulletin ATR72–92–1032, dated June 6, 2013. 

(5) Avions de Transport Re ́gional Service 

Bulletin ATR72–92–1032, Revision 01, dated 

January 16, 2014. 

(6) Avions de Transport Re ́gional Service 

Bulletin ATR72–92–1032, Revision 02, dated 

April 17, 2014. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the actions 

must be accomplished using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the EASA; or ATR–GIE 

Avions de Transport Re ́gional’s EASA DOA. 

If approved by the DOA, the approval must 

include the DOA-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0171, dated 

August 20, 2015, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-1280-0003. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available 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 this AD specifies otherwise. 

mstockstill on DSK4VPTVN1PROD with RULES

Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations 9749 

(i) Avions de Transport Re ́gional Service 

Bulletin ATR42–92–0024, Revision 03, dated 

January 21, 2015. 

(ii) Avions de Transport Re ́gional Service 

Bulletin ATR72–92–1032, Revision 03, dated 

January 21, 2015. 

(3) For service information identified in 

this AD, contact ATR–GIE Avions de 

Transport Re ́gional, 1, Alle ́e Pierre Nadot, 

31712 Blagnac Cedex, France; telephone +33 

(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; 

email continued.airworthiness@atr.fr; 

Internet http://www.aerochain.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 February 

16, 2016. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–03689 Filed 2–25–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3146; Directorate 

Identifier 2014–NM–249–AD; Amendment 

39–18411; AD 2016–04–17] 

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 certain 

The Boeing Company Model 777–200 

series airplanes. This AD was prompted 

by an evaluation by the design approval 

holder (DAH) indicating that the skin 

lap splices at certain stringers in certain 

fuselage sections are subject to 

widespread fatigue damage (WFD) on 

aging Model 777 airplanes that have 

accumulated at least 45,000 total flight 

cycles. This AD requires inspections to 

detect cracking of fuselage skin lap 

splices in certain fuselage sections, and 

corrective actions if necessary; 

modification of left-side and right-side 

lap splices; and post-modification 

repetitive inspections for cracks in the 

modified lap splices, and corrective 

actions if necessary. We are issuing this 

AD to detect and correct fatigue 

cracking of the skin lap splices, and 

consequent risk of sudden 

decompression and the inability to 

sustain limit flight and pressure loads. 

DATES: This AD is effective April 1, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 1, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3146. 

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– 

3146; 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: Eric 

Lin, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6412; fax: 425– 

917–6590; email: Eric.Lin@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 certain The Boeing Company 

Model 777–200 series airplanes. The 

NPRM published in the Federal 

Register on August 25, 2015 (80 FR 

51488) (‘‘the NPRM’’). The NPRM was 

prompted by an evaluation by the DAH 

indicating that the skin lap splices at 

certain stringers in certain fuselage 

sections are subject to WFD on aging 

airplanes (airplanes that have 

accumulated at least 45,000 total flight 

cycles). The NPRM proposed to require 

inspections to detect cracking of 

fuselage skin lap splices in certain 

fuselage sections, and corrective actions 

if necessary; modification of left-side 

and right-side lap splices; and postmodification repetitive inspections for 

cracks in the modified lap splices, and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

fatigue cracking of the skin lap splices, 

and consequent risk of sudden 

decompression and the inability to 

sustain limit flight and pressure loads. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Support for the NPRM 

An anonymous commenter expressed 

support for the NPRM. 

Request To Revise WFD Criteria 

Definition 

Boeing requested that we revise the 

NPRM to specify that DAH analysis 

indicates that potential multi-site 

damage that could lead to WFD does not 

occur until at least 45,000 total flight 

cycles on aging Model 777 airplanes. 

We agree with the commenter’s 

request. We have revised the SUMMARY

and Discussion sections of this final rule 

and paragraph (e) of this AD to specify 

that this AD was prompted by an 

evaluation by the DAH indicating that 

the skin lap splices at certain stringers 

in certain fuselage sections are subject 

to WFD on aging Model 777 airplanes 

that have accumulated at least 45,000 

total flight cycles. 

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 changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

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