Federal Register / Vol. 80, No. 217 / Tuesday, November 10, 2015 / Rules and Regulations 69569 

deployment, or stowed components 

where applicable, must also be taken 

into account. 

7. Inadvertent deployment of the 

structure-mounted airbag during the 

most critical part of flight will either not 

cause a hazard to the airplane or is 

extremely improbable. 

8. The applicant must demonstrate 

that the structure-mounted airbag, when 

deployed, does not impair access to the 

seatbelt- or harness-release means, and 

must not hinder evacuation. This will 

include consideration of adjacent seat 

places and the aisle. 

9. The airbag, once deployed, must 

not adversely affect the emergencylighting system, and must not block 

escape-path lighting to the extent that 

the light(s) no longer meet their 

intended function. 

10. The structure-mounted airbag 

must not impede occupants’ rapid exit 

from the airplane 10 seconds after its 

deployment. 

11. Where structure-mounted airbag 

systems are installed in or close to 

passenger evacuation routes (other than 

for the passenger seat for which the 

airbag is installed), possibility of impact 

on emergency evacuation (e.g., hanging 

in the aisle, potential trip hazard, etc.) 

must be evaluated. 

12. The airbag electronic system must 

be designed to be protected from 

lightning per 14 CFR 25.1316(b), and 

high-intensity radiated fields (HIRF) per 

14 CFR 25.1317(c). 

13. The structure-mounted airbag 

system must not contain or release 

hazardous quantities of gas or 

particulate matter into the cabin. 

14. The structure-mounted airbag 

installation must be protected from the 

effects of fire such that no hazard to 

occupants will result. 

15. The inflatable bag material must 

meet the 2.5-inches-per-minute 

horizontal flammability test defined in 

14 CFR part 25, appendix F, part I, 

paragraph (a)(1)(iv). 

16. The design of the structuremounted airbag system must protect the 

mechanisms and controls from external 

contamination associated with that 

which could occur on or around 

passenger seating. 

17. The structure-mounted airbag 

system must have a means to verify the 

integrity of the structure-mounted airbag 

activation system. 

18. The applicant must provide 

installation limitations to ensure 

installation compatibility between the 

seat design and opposing monument or 

structure. 

Issued in Renton, Washington, on October 

30, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–28568 Filed 11–9–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3620; Directorate 

Identifier 2015–CE–029–AD; Amendment 

39–18319; AD 2015–23–03] 

RIN 2120–AA64 

Airworthiness Directives; Pacific 

Aerospace Limited Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) AD 2014– 

20–13 for certain Pacific Aerospace 

Limited Model 750XL airplanes. This 

AD results from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as fatigue cracks on the fin 

forward pickup plates, which could 

cause it to fail. We are issuing this AD 

to require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective December 

15, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 15, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3620; 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 20590. 

For service information identified in 

this AD, contact Pacific Aerospace 

Limited, Airport Road, Hamilton, 

Private Bag 3027, Hamilton 3240, New 

Zealand, phone: +64 7 843 6144; fax: 

+64 7 843 6134; email: pacific@

aerospace.co.nz; Internet: 

www.aerospace.co.nz. You may view 

this referenced service information at 

the FAA, Small Airplane Directorate, 

901 Locust, Kansas City, Missouri 

64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

Docket No. FAA–2015–3620. 

FOR FURTHER INFORMATION CONTACT: Karl 

Schletzbaum, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4123; fax: (816) 

329–4090; email: karl.schletzbaum@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to add an AD that would apply 

to certain Pacific Aerospace Limited 

Model 750XL airplanes. That NPRM 

was published in the Federal Register 

on August 27, 2015 (80 FR 51966), and 

proposed to supersede AD 2014–20–13, 

Amendment 39–17986 (79 FR 60329, 

October 7, 2014). 

Since we issued AD 2014–20–13, 

Amendment 39–17986 (79 FR 60329, 

October 7, 2014), Pacific Aerospace 

Limited has revised the related service 

information and developed a 

terminating action for the repetitive 

inspections. 

The Civil Aviation Authority (CAA), 

which is the aviation authority for New 

Zealand, has issued AD DCA/750XL/

18A, dated August 4, 2015 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

DCA/750XL/18A revised to add note 2 and 

introduce minor editorial changes. This AD 

supersedes DCA/750XL/18 and DCA/750XL/ 

16A to introduce the requirements in Pacific 

Aerospace Limited Mandatory Service 

Bulletin (MSB) PACSB/XL/068 issue 5, dated 

29 June 2015. The revised MSB introduces a 

life limit for fin forward pickup P/N 11– 

10281–1 and reduces the torque setting for 

the fin forward pickup bolt to alleviate some 

of the loads applied to the pickup. The MSB 

also introduces a replacement fin forward 

pickup P/N 11–03375–1 which is not life 

limited. 

You may examine the MCAI on the 

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

#!documentDetail;D=FAA-2015-3620- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 51966, August 27, 2015) or on the 

determination of the cost to the public. 


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69570 Federal Register / Vol. 80, No. 217 / Tuesday, November 10, 2015 / Rules and Regulations 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 

51966, August 27, 2015) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 51966, 

August 27, 2015). 

Related Service Information Under 1 

CFR Part 51 

We reviewed Pacific Aerospace 

Limited Mandatory Service Bulletin 

PACSB/XL/068, Issue 5, dated June 29, 

2015. The service bulletin describes 

procedures for reducing the torque 

setting for the fin forward pickup bolt. 

The service bulletin also introduces a 

new, improved replacement fin forward 

pickup plate, part number (P/N) 11– 

0375–1, to replace P/N 11–10281–1. 

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 of 

this AD. 

Costs of Compliance 

We estimate that this AD will affect 

18 products of U.S. registry. We also 

estimate that it will take about 22 workhours per product to comply with all 

the requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $1,692 

per product. 

Based on these figures, we estimate 

the cost of this AD on U.S. operators to 

be $64,116, or $3,562 per product. 

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 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 by searching for 

and locating Docket No. FAA–2015– 

3620; 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 the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone (800) 647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

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 Amendment 39–17986 (79 FR 

60329, October 7, 2014) and adding the 

following new AD: 

2015–23–03 Pacific Aerospace Limited: 

Amendment 39–18319; Docket No. 

FAA–2015–3620; Directorate Identifier 

2015–CE–024–AD. 

(a) Effective Date 

This Airworthiness Directive (AD) becomes 

effective December 15, 2015. 

(b) Affected ADs 

This AD replaces AD 2014–20–13, 

Amendment 39–17986 (79 FR 60329, October 

7, 2014). 

(c) Applicability 

This AD applies to Pacific Aerospace 

Limited Model 750XL airplanes, all serial 

numbers through XL–193, XL–195, and XL– 

197, certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 53: Fuselage. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as fatigue 

cracks on the fin forward pickup plates. We 

are issuing this AD to detect and correct 

cracked fin forward pickup plates to prevent 

failure of the fin forward pickup plates, 

which could result in reduced control. 

(f) Actions and Compliance 

Unless already done, do the actions in 

paragraphs (f)(1) through (f)(4) of this AD: 

(1) Within the next 150 hours time-inservice (TIS) after December 15, 2015 (the 

effective date of this AD), reduce the fin 

forward pickup bolt torque following the 

procedures in section 1.D., paragraphs A. 1) 

and A. 2) of the PLANNING INFORMATION 

in Pacific Aerospace Limited Mandatory 

Service Bulletin PACSB/XL/068, Issue 5, 

dated June 29, 2015. 

(2) At or before reaching 2,000 hours total 

time-in-service (TTIS) or within the next 150 

hours TIS after December 15, 2015 (the 

effective date of this AD), whichever occurs 

later, and repetitively thereafter at intervals 

not to exceed 600 hours TIS or 12 months, 

whichever occurs first, do a detailed visual 

inspection and liquid penetrant inspection of 

the fin forward pickup plates for any 

evidence of cracking. Do the inspections 

following the procedures in sections 2.A. and 

2.B. of the ACCOMPLISHMENT 

INSTRUCTIONS in Pacific Aerospace 

Limited Mandatory Service Bulletin PACSB/ 

XL/068, Issue 5, dated June 29, 2015. 

(3) If cracks are found during any 

inspection required in paragraph (f)(2) of this 

AD, before further flight, replace the fin 

forward pickup plates with new fin forward 

pickup plates, part number (P/N) 11–03375– 

1. Do the replacement following the 

procedures in section 2.C. of the 

ACCOMPLISHMENT INSTRUCTIONS in 

Pacific Aerospace Limited Mandatory Service 

Bulletin PACSB/XL/068, Issue 5, dated June 


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Federal Register / Vol. 80, No. 217 / Tuesday, November 10, 2015 / Rules and Regulations 69571 

29, 2015. This replacement terminates the 

repetitive inspections required in paragraph 

(f)(2) of this AD. 

(4) If no cracks are found during any 

inspection required in paragraph (f)(2) of this 

AD, at or before reaching 6,000 hours TTIS 

or within the next 600 hours TIS after 

December 15, 2015 (the effective date of this 

AD), whichever occurs later, replace the fin 

forward pickup plates, P/N 11–10281–1, with 

P/N 11–03375–1. Do the replacement 

following the procedures in section 2.D. of 

the ACCOMPLISHMENT INSTRUCTIONS in 

Pacific Aerospace Limited Mandatory Service 

Bulletin PACSB/XL/068, Issue 5, dated June 

29, 2015. This replacement terminates the 

repetitive inspections required in paragraph 

(f)(2) of this AD . 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Karl Schletzbaum, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4146; fax: (816) 

329–4090; email: karl.schletzbaum@faa.gov. 

Before using any approved AMOC on any 

airplane to which the AMOC applies, notify 

your appropriate principal inspector (PI) in 

the FAA Flight Standards District Office 

(FSDO), or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(h) Related Information 

Refer to MCAI Civil Aviation Authority 

(CAA) AD DCA/750XL/18A, dated August 4, 

2015, for related information. You may 

examine the MCAI on the Internet at 

http://www.regulations.gov/

#!documentDetail;D=FAA-2015-3620-0002. 

(i) 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) Pacific Aerospace Limited Mandatory 

Service Bulletin PACSB/XL/068, Issue 5, 

dated June 29, 2015. 

(ii) Reserved. 

(3) For Pacific Aerospace Limited service 

information identified in this AD, contact 

Pacific Aerospace Limited, Airport Road, 

Hamilton, Private Bag 3027, Hamilton 3240, 

New Zealand, phone: +64 7 843 6144; fax: 

+64 7 843 6134; email: pacific@

aerospace.co.nz; Internet: 

www.aerospace.co.nz. 

(4) You may view this service information 

at FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call 816–329–4148. In 

addition, you can access this service 

information on the Internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2015–3620. 

(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 Kansas City, Missouri, on 

November 2, 2015. 

Melvin Johnson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–28338 Filed 11–9–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1008; Directorate 

Identifier 2013–SW–064–AD; Amendment 

39–18317; AD 2015–23–01] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Type Certificate 

Previously Held by Schweizer Aircraft 

Corporation) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Sikorsky Aircraft Corporation (Sikorsky) 

Model 269A, 269A–1, 269B, 269C, 

269C–1, 269D, and TH–55A helicopters. 

This AD requires repetitively inspecting 

and lubricating the tail rotor (T/R) 

driveshaft splined fittings. This AD was 

prompted by a report that the T/R 

driveshaft can disconnect due to 

deterioration of the splined coupling. 

The actions are intended to detect and 

prevent excessive wear of the splined 

coupling, which could lead to failure of 

the T/R driveshaft and subsequent loss 

of control of the helicopter. 

DATES: This AD is effective December 

15, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of December 15, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Sikorsky 

Aircraft Corporation, Customer Service 

Engineering, 124 Quarry Road, 

Trumbull, CT 06611; telephone 1–800– 

Winged–S or 203–416–4299; email 

sikorskywcs@sikorsky.com. You may 

review a copy of the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy., Room 6N–321, 

Fort Worth, TX 76177. 

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– 

1008; 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, any incorporated-byreference 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: 

Stephen Kowalski, Aviation Safety 

Engineer, New York Aircraft 

Certification Office, Engine & Propeller 

Directorate, 1600 Stewart Ave., Suite 

410, Westbury, NY 11590; telephone 

(516) 228–7327; email 

stephen.kowalski@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On April 22, 2015, at 80 FR 22436, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 by 

adding an AD that would apply to 

Sikorsky Model 269A, 269A–1, 269B, 

269C, 269C–1, 269D, and TH–55A 

helicopters. The NPRM proposed to 

require, within 100 hours time-inservice (TIS), a one-time inspection and 

lubrication of the T/R driveshaft splined 

fittings and replacing a splined fitting 

and the T/R driveshaft if the fitting has 

excessive wear. If the helicopter has a T/ 

R driveshaft grease fitting installed, the 

NPRM also proposed to require 

inspecting each grease fitting for certain 

conditions and replacing the grease 

fitting if necessary. The NPRM also 

proposed to require, at intervals not 

exceeding 100 hours TIS, inspecting the 

T/R driveshaft for straightness, twists, 

and scratches; inspecting each forward 

and aft T/R driveshaft splines for wear; 

and correcting the torque of each main 

transmission aft pinion nut. The 

proposed requirements were prompted 


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