Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations 26673 

13. The airbag system in the shoulderbelt installation must be protected from 

the effects of fire such that no hazard to 

occupants will result. 

14. A means must be available for a 

crewmember to verify the integrity of 

the airbag system in the shoulder-belt 

activation system prior to each flight, or 

it must be demonstrated to reliably 

operate between inspection intervals. 

The FAA considers that the loss of the 

airbag-system deployment function 

alone (i.e., independent of the 

conditional event that requires the 

airbag-system deployment) is a majorfailure condition. 

15. The inflatable material may not 

have an average burn rate of greater than 

2.5 inches/minute when tested using the 

horizontal flammability test defined in 

part 25, appendix F, part I, paragraph 

(b)(5). 

16. The airbag system in the shoulder 

belt, once deployed, must not adversely 

affect the emergency-lighting system 

(i.e., block floor proximity lights to the 

extent that the lights no longer meet 

their intended function). 

Issued in Renton, Washington, on April 27, 

2016. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–10440 Filed 5–3–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3982; Directorate 

Identifier 2015–NM–098–AD; Amendment 

39–18503; AD 2016–09–05] 

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 717–200 

airplanes. This AD was prompted by 

multiple reports of the vertical stabilizer 

leading edge showing signs of fastener 

distress. This AD requires a detailed 

inspection for any distress of the 

vertical stabilizer leading edge skin, and 

related investigative and corrective 

actions if necessary. This AD also 

requires, for certain airplanes, repetitive 

detailed inspections of the spar cap for 

any loose and missing fasteners, 

repetitive eddy current testing high 

frequency (ETHF) and radiographic 

testing (RT) inspections of the spar cap 

for any crack, and related investigative 

and corrective actions if necessary. We 

are issuing this AD to detect and correct 

any crack in the vertical stabilizer 

leading edge and front spar cap, which 

may result in the structure becoming 

unable to support limit load, and may 

lead to the loss of the vertical stabilizer. 

DATES: This AD is effective June 8, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 8, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Data & Services Management, 

3855 Lakewood Boulevard, MC D800– 

0019, Long Beach, CA 90846–0001; 

telephone: 206–544–5000, extension 2; 

fax: 206–766–5683; 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– 

3982. 

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– 

3982; 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 

Schrieber, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 

562–627–5348; fax: 562–627–5210; 

email: Eric.Schrieber@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 717–200 airplanes. The NPRM 

published in the Federal Register on 

October 6, 2015 (80 FR 60307) (‘‘the 

NPRM’’). The NPRM was prompted by 

multiple reports of the vertical stabilizer 

leading edge showing signs of fastener 

distress. The NPRM proposed to require 

a detailed inspection for any distress of 

the vertical stabilizer leading edge skin, 

and related investigative and corrective 

actions if necessary. The NPRM also 

proposed to require, for certain 

airplanes, repetitive detailed 

inspections of the spar cap for any loose 

and missing fasteners, repetitive ETHF 

and RT inspections of the spar cap for 

any crack, and related investigative and 

corrective actions if necessary. We are 

issuing this AD to detect and correct any 

crack in the vertical stabilizer leading 

edge and front spar cap, which may 

result in the structure becoming unable 

to support limit load, and may lead to 

the loss of the vertical stabilizer. 

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. Boeing and 

an anonymous commenter indicated 

their support for the NPRM. 

Request To Add Credit for Previous 

Actions 

Boeing requested that we add a 

‘‘Credit for Previous Actions’’ paragraph 

to the proposed AD that would give 

credit for prior accomplishment of the 

initial inspection in paragraph (g) of the 

NPRM. Boeing stated that operator 

structural inspection credit has been 

incorporated as a precedent in previous 

ADs. 

We agree with the commenter’s 

request. Boeing MOM–MOM–14–0437– 

01B(R1), dated July 3, 2014, provides 

the same action and level of safety for 

the initial inspection specified in this 

AD. We have revised this AD by adding 

new paragraph (j) of this AD to give 

credit for the initial inspection in 

paragraph (g) of this AD, if that 

inspection was performed before the 

effective date of this AD using Boeing 

MOM–MOM–14–0437–01B(R1), dated 

July 3, 2014. We have redesignated the 

remaining paragraphs accordingly. 

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 


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26674 Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations 

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 

We reviewed Boeing Alert Service 

Bulletin 717–55A0012, dated June 12, 

2015. The service information describes 

procedures for a detailed inspection for 

any distress of the vertical stabilizer 

leading edge skin, a detailed inspection 

for any loose and missing fasteners of 

the spar cap, ETHF and RT inspections 

of the spar cap for any crack, and related 

investigative and corrective actions. 

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 106 

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 

Inspections for distress .......................... 11 work-hours × $85 per hour = $935 

per inspection cycle.

$0 $935 per inspection 

cycle.

$99,110 per inspection cycle. 

Repetitive inspections for cracking and 

loose and missing fasteners.

7 work-hours × $85 per hour = $595 

per inspection cycle.

0 595 per inspection 

cycle.

63,070 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. 

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): 

2016–09–05 The Boeing Company: 

Amendment 39–18503; Docket No. 

FAA–2015–3982; Directorate Identifier 

2015–NM–098–AD. 

(a) Effective Date 

This AD is effective June 8, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 717–200 airplanes, certificated in any 

category, as specified in Boeing Alert Service 

Bulletin 717–55A0012, dated June 12, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55, Stabilizers. 

(e) Unsafe Condition 

This AD was prompted by multiple reports 

of the vertical stabilizer leading edge 

showing signs of fastener distress. We are 

issuing this AD to detect and correct any 

crack in the vertical stabilizer leading edge 

and front spar cap, which may result in the 

structure becoming unable to support limit 

load, and may lead to the loss of the vertical 

stabilizer. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Initial Inspection 

Except as required by paragraph (i)(1) of 

this AD, at the applicable time specified in 

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

Alert Service Bulletin 717–55A0012, dated 

June 12, 2015: Do a detailed inspection for 

any distress of the vertical stabilizer leading 

edge skin and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

717–55A0012, dated June 12, 2015, except as 

required by paragraph (i)(2) of this AD. Do all 

applicable related investigative and 

corrective actions before further flight. 

(h) Repetitive Inspections 

For all airplanes on which no cracking was 

found during any related investigative action 

required by paragraph (g) of this AD: At the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 717–55A0012, dated June 12, 2015, 

do the actions specified in paragraphs (h)(1) 

and (h)(2) of this AD and do all applicable 

related investigative and corrective actions, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 


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Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations 26675 

717–55A0012, dated June 12, 2015, except as 

required by paragraph (i)(2) of this AD. Do all 

applicable related investigative and 

corrective actions before further flight. 

Repeat the applicable inspection thereafter at 

the intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 717–55A0012, dated June 12, 2015. 

(1) Do detailed inspections for any loose 

and missing fasteners of the vertical stabilizer 

leading edge as specified in ‘‘Part 4’’ of 

Boeing Alert Service Bulletin 717–55A0012, 

dated June 12, 2015. 

(2) Do eddy current testing high frequency 

(ETHF) and radiographic testing (RT) 

inspections for any crack of the vertical 

stabilizer spar cap as specified in ‘‘Part 2’’ of 

Boeing Alert Service Bulletin 717–55A0012, 

dated June 12, 2015; or do ETHF inspections 

for any crack of the vertical stabilizer spar 

cap as specified in ‘‘Part 3’’ of Boeing Alert 

Service Bulletin 717–55A0012, dated June 

12, 2015. 

(i) Exceptions to the Service Information 

(1) Where Boeing Alert Service Bulletin 

717–55A0012, dated June 12, 2015 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 any crack is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 717–55A0012, dated 

June 12, 2015, specifies to contact Boeing for 

appropriate action: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

initial inspection specified in paragraph (g) 

of this AD, if that inspection was performed 

before the effective date of this AD using 

Boeing MOM–MOM–14–0437–01B(R1), 

dated July 3, 2014, which is not incorporated 

by reference in this AD. 

(k) 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 (l) of this AD. Information may be 

emailed to: 9-ANM-LAACO-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, Los Angeles 

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. 

(l) Related Information 

For more information about this AD, 

contact Eric Schrieber, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles ACO, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5348; fax: 562–627–5210; email: 

Eric.Schrieber@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 717– 

55A0012, dated June 12, 2015. 

(ii) Reserved. 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, 3855 Lakewood 

Boulevard, MC D800–0019, Long Beach, CA 

90846–0001; telephone: 206–544–5000, 

extension 2; fax: 206–766–5683; 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 20, 

2016. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–10160 Filed 5–3–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–7490; Directorate 

Identifier 2015–NE–40–AD; Amendment 39– 

18500; AD 2016–09–02] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Turbomeca S.A. Astazou XIV B and H 

turboshaft engines. This AD requires a 

one-time inspection of the front surface 

of the 3rd stage turbine for a groove. 

This AD was prompted by a report of a 

crack on the 3rd stage turbine wheel. 

We are issuing this AD to prevent cracks 

in the 3rd stage turbine wheel, failure of 

the engine, in-flight shutdown, and loss 

of control of the helicopter. 

DATES: This AD becomes effective June 

8, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 8, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Turbomeca S.A., 40220 Tarnos, France; 

phone: 33 (0)5 59 74 40 00; fax: 33 (0)5 

59 74 45 15. 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. 

It is also available on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2015– 

7490. 

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– 

7490; 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 mandatory 

continuing airworthiness information 

(MCAI), the regulatory evaluation, any 

comments received, and other 

information. The address for the Docket 

Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Wego Wang, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7134; fax: 781–238–7199; 

email: wego.wang@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 the specified products. The 


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