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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9750 Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 777–53A0052, dated October 

10, 2014. The service bulletin describes 

procedures for inspections to detect 

cracking of fuselage skin lap splices, 

modification to the skin lap splices, 

repetitive inspections for cracks in the 

modified lap splices, and repairs. 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 21 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

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

Inspection and modification.2,713 work-hours × $85 per hour = $230,605 ... $0 $230,605 ...................... $4,842,705. 

Post-modification inspection.1,391 work-hours × $85 per hour = $118,235 

per inspection cycle.

0 $118,235 per inspection 

cycle.

$2,482,935 per inspection cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all available costs in our 

cost estimate. 

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): 

2016–04–17 The Boeing Company: 

Amendment 39–18411; Docket No. 

FAA–2015–3146; Directorate Identifier 

2014–NM–249–AD. 

(a) Effective Date 

This AD is effective April 1, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200 series airplanes, certificated 

in any category, as identified in Boeing Alert 

Service Bulletin 777–53A0052, dated October 

10, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder indicating that 

the skin lap splices at certain stringers in 

certain fuselage sections are subject to 

widespread fatigue damage on aging Model 

777 airplanes that have accumulated at least 

45,000 total flight cycles. 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. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections and Corrective Actions 

Except as provided by paragraph (h)(1) of 

this AD, at the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 777–53A0052, dated 

October 10, 2014: Do Part 1, inspection ‘‘A,’’ 

of the modification area for cracks; Part 2, 

inspection ‘‘B,’’ of the modification area for 

cracks; and Part 3, inspection ‘‘C,’’ of the 

modification area for scribe lines and cracks; 

as applicable; and do all applicable 

corrective actions; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–53A0052, dated October 

10, 2014, except as provided by paragraph 

(h)(2) of this AD. Do all applicable corrective 

actions before further flight. 

(1) Inspection ‘‘A’’ includes an external 

phased array ultrasonic inspection for cracks 

in the lower/overlapped skin of the stringer 

S–14 left and right (L/R) lap splices between 

fuselage station 655 and station 1434, and an 

open hole high frequency eddy current 

(HFEC) inspection for skin cracks at the 

upper and lower fastener rows of the stringer 

S–14 L/R lap splices. 

(2) Inspection ‘‘B’’ includes the inspections 

specified in paragraphs (g)(2)(i) through 

(g)(2)(iv) of this AD. 

(i) A detailed inspection for cracks of any 

skin panel common to a stringer S–14 L/R lap 

splice between fuselage station 655 and 

station 1434 that has a scribe line 0.001 inch 

or deeper. 

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Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations 9751 

(ii) Either an ultrasonic inspection or a 

surface HFEC inspection for cracks 

(depending on the location of the scribe 

line(s)) of any skin panel common to a 

stringer S–14 L/R lap splice between fuselage 

station 655 and station 1434 that has a scribe 

line 0.001 inch or deeper. 

(iii) An external phased array ultrasonic 

inspection for cracks in the lower/overlapped 

skin of the stringer S–14 L/R lap splices 

between fuselage station 655 and station 

1434. 

(iv) An open hole HFEC inspection for skin 

cracks at the upper and lower fastener rows 

of the stringer S–14 L/R lap splices. 

(3) Inspection ‘‘C’’ includes the inspections 

for scribe lines and cracks specified in 

paragraphs (g)(3)(i), (g)(3)(ii), and (g)(3)(iii) of 

this AD on stringer S–14 L/R lap splice 

between fuselage station 655 and station 

1434 on both sides of the airplane. 

(i) A detailed inspection for scribe lines. If 

any scribe line is found during the inspection 

required by this paragraph, the actions 

include the inspections specified in 

paragraphs (g)(3)(i)(A) and (g)(3)(i)(B) of this 

AD. 

(A) A detailed inspection for cracks of the 

scribe line area(s). 

(B) Either an ultrasonic inspection or a 

surface HFEC inspection for cracks 

(depending on the location of the scribe 

line(s)). 

(ii) An external phased array ultrasonic 

inspection for cracks in the lower/overlapped 

skin of the stringer S–14 L/R lap splices 

between fuselage station 655 and station 

1434. 

(iii) An open hole HFEC inspection for skin 

cracks at the upper and lower fastener rows 

of the stringer S–14 L/R lap splices. 

(h) Exceptions to Service Information 

Specifications 

(1) Where Paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–53A0052, 

dated October 10, 2014, specifies a 

compliance time ‘‘after the original issue date 

of this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time ‘‘after the effective date of this AD.’’ 

(2) If, during accomplishment of any 

inspection required by this AD, any 

condition is found for which Boeing Alert 

Service Bulletin 777–53A0052, dated October 

10, 2014, specifies to contact Boeing for 

special repair instructions or supplemental 

instructions for the modification, and 

specifies that action as ‘‘RC’’ (Required for 

Compliance): Before further flight, do the 

repair or modification using a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD. 

(i) Lap Splice Modification 

At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 777–53A0052, dated 

October 10, 2014: Do the left-side and rightside lap splice modification, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 777–53A0052, 

dated October 10, 2014, except as provided 

by paragraph (h)(2) of this AD. 

(j) Post-Modification Inspections and 

Corrective Action 

At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 777–53A0052, dated 

October 10, 2014: Do a post-modification 

internal surface HFEC inspection for skin 

cracks in the modified lap splices on both 

sides of the airplane; and do all applicable 

corrective actions; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–53A0052, dated October 

10, 2014, except as provided by paragraph 

(h)(2) of this AD. Do all applicable corrective 

actions before further flight. Repeat the 

inspection of the modified lap splices 

thereafter at the applicable intervals specified 

in paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 777–53A0052, dated 

October 10, 2014. 

(k) 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 (l) 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) Except as required by paragraph (h)(2) 

of this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (k)(4)(i) and (k)(4)(ii) 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. 

(l) Related Information 

For more information about this AD, 

contact Eric Lin, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6412; fax: 425– 

917–6590; email: Eric.Lin@faa.gov. 

(m) 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 777– 

53A0052, dated October 10, 2014. 

(ii) Reserved. 

(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. 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. 2016–03886 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–2015–2984; Directorate 

Identifier 2015–NE–21–AD; Amendment 39– 

18405; AD 2016–04–11] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

General Electric Company (GE) GEnx– 

1B54, –1B58, –1B64, –1B67, and –1B70 

turbofan engine models. This AD was 

prompted by reports of two separate, 

single engine in-flight shutdowns 

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