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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69572 Federal Register / Vol. 80, No. 217 / Tuesday, November 10, 2015 / Rules and Regulations 

by a report of excessive spline wear on 

the forward and aft T/R driveshaft 

spined fittings. The proposed 

requirements were intended to prevent 

failure of the T/R driveshaft and 

subsequent loss of control of the 

helicopter. 

Since the NPRM was issued, the FAA 

Southwest Regional Office has 

relocated. We have revised the contact 

information throughout this Final Rule 

to reflect the new address. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (80 FR 22436, April 22, 2015). 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Sikorsky 269 Alert 

Service Bulletin (ASB) B–299.1 for 

Model 269A, 269A–1, 269B, 269C, and 

TH–55A helicopters; 269C–1 ASB C1B– 

036.1 for Model 269C–1 helicopters; and 

269D ASB DB–041.1 for Model 269D 

helicopters, each Revision 1 and dated 

February 24, 2012. Each ASB describes 

procedures for cleaning, inspecting, and 

lubricating the forward and aft T/R 

driveshaft splined fittings and returning 

to Sikorsky any parts that exceed wear 

limits. Each ASB also requires 

implementing a 100-hour TIS recurring 

inspection of the T/R driveshaft, 

coupling and internal stop, coupling 

drive splines, and the pinion nut by 

following the procedures in each model 

helicopter’s Handbook of Maintenance 

Instructions. 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. 

Differences Between This AD and the 

Service Information 

The Sikorsky ASBs require returning 

any splined fittings that exceed wear 

limits to Sikorsky, while this AD 

requires replacing those fittings and the 

T/R driveshaft. 

Costs of Compliance 

We estimate that this AD will affect 

1,085 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD. At an average labor rate of $85 

per work-hour, inspecting and 

lubricating the T/R driveshaft splined 

fittings requires 1.8 hours, for a cost per 

helicopter of $153 and a total cost of 

$166,005 for the fleet. Inspecting the 

grease fittings requires 0.25 hour, for a 

cost of $21 per helicopter and a total 

cost of $22,785 for the fleet. Inspecting 

the driveshaft, fittings, internal stops, 

and drive spines requires 1.8 hours, for 

a cost per helicopter of $153 and a total 

cost of $166,005 for the fleet, per 

inspection cycle. 

If required, replacing the T/R driving 

spline and driveshaft requires 1.6 workhours, and required parts will cost about 

$14,853, for a cost per helicopter of 

$14,989. 

If required, replacing a T/R driven 

spline and driveshaft requires 1.5 workhours, and required parts will cost about 

$14,836, for a cost per helicopter of 

$14,964. 

If required, replacing a grease fitting 

requires about 0.25 work-hour, and 

required parts will cost about $5, for a 

cost per helicopter of $26. 

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 to the extent that it justifies 

making a regulatory distinction; and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2015–23–01 Sikorsky Aircraft Corporation 

(Type Certificate Previously Held by 

Schweizer Aircraft Corporation) 

Helicopters: Amendment 39–18317; 

Docket No. FAA–2015–1008; Directorate 

Identifier 2013–SW–064–AD. 

(a) Applicability 

This AD applies to Sikorsky Aircraft 

Corporation (Sikorsky) Model 269A, 269A–1, 

269B, 269C, 269C–1, 269D, and TH–55A 

helicopters, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

insufficient lubrication of a tail rotor (T/R) 

driveshaft splined fitting. This condition 

could result in excessive wear of the T/R 

driveshaft splines, which could lead to 

failure of the T/R driveshaft and subsequent 

loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective December 15, 

2015. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1)Within 100 hours time-in-service (TIS): 

(i) Inspect each T/R driveshaft splined 

fitting for a crack, a break, excessive wear, 


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Federal Register / Vol. 80, No. 217 / Tuesday, November 10, 2015 / Rules and Regulations 69573 

galling, spalling, chipping, corrosion, heat 

discoloration, and distortion by following the 

Accomplishment Instructions, paragraphs 

3.B.(1) through 3.B.(2), of Sikorsky 269 Alert 

Service Bulletin (ASB) B–299.1 for Model 

269A, 269A–1, 269B, 269C, and TH–55A 

helicopters; 269C–1 ASB C1B–036.1 for 

Model 269C–1 helicopters; or 269D ASB DB– 

041.1 for Model 269D helicopters, each 

Revision 1 and dated February 24, 2012. If 

there is a crack, a break, excessive wear, 

galling, spalling, chipping, corrosion, heat 

discoloration, or distortion on any T/R 

driveshaft splined fitting, before further 

flight, replace the affected splined fitting and 

the T/R driveshaft. 

(ii) If installed, inspect each T/R driveshaft 

grease fitting for looseness, presence of a 

check ball inside each fitting, and for proper 

operation and seating of each check ball. If 

any grease fitting is loose, missing a check 

ball, fails to properly operate, or if a check 

ball fails to seat, before further flight, replace 

the grease fitting. 

(iii) Lubricate each driveshaft fitting by 

following the Accomplishment Instructions, 

paragraph 3.B.(6), of Sikorsky 269 ASB B– 

299.1 for Model 269A, 269A–1, 269B, 269C, 

and TH–55A helicopters; 269C–1 ASB C1B– 

036.1 for Model 269C–1 helicopters; or 269D 

ASB DB–041.1 for Model 269D helicopters, 

each Revision 1 and dated February 24, 2012. 

(2) Within 100 hours TIS after the 

inspections required by paragraph (e)(1) of 

this AD, and thereafter at intervals not 

exceeding 100 hours TIS: 

(i) Remove the driveshaft from the gearbox 

and clean any grease from each end fitting. 

(ii) Inspect the driveshaft for straightness, 

a twist, and a scratch. If the driveshaft has 

any bends, twists, or scratches, before further 

flight, replace the driveshaft. 

(iii) Inspect the internal splines of each 

forward and aft fitting and each internal stop 

for wear. If there is any wear, before further 

flight, replace the fitting. 

(iv) Inspect the drive splines of each 

splined drive fitting for wear. If there is any 

wear, before further flight, replace the 

splined drive fitting. 

(v) Loosen the aft frame clamp and apply 

a torque of 750 to 1,000 inch-pounds to each 

main transmission aft pinion nut. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, New York Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

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. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6500, Tail Rotor Drive. 

(h) 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) Sikorsky 269 Alert Service Bulletin 

(ASB) B–299.1, Revision 1, dated February 

24, 2012. 

(ii) Sikorsky 269C–1 ASB C1B–036.1, 

Revision 1, dated February 24, 2012. 

(iii) Sikorsky 269D ASB DB–041.1, 

Revision 1, dated February 24, 2012. 

(3) For Sikorsky 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. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on October 30, 

2015. 

James A. Grigg, 

Acting Assistant Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–28313 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–2014–0574; Directorate 

Identifier 2013–NM–258–AD; Amendment 

39–18315; AD 2015–22–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A318, A319, A320, and 

A321 series airplanes. This AD was 

prompted by a report of skin disbonding 

on a composite side shell panel of a 

rudder. This AD requires an inspection 

to determine if any rudder composite 

side shell panel has been repaired, a 

thermography inspection of each rudder 

that has received this repair, and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct skin disbonding on 

the rudder, which could affect the 

structural integrity of the rudder, 

possibly resulting in reduced control of 

the airplane. 

DATES: This AD becomes effective 

December 15, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 15, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0574 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 AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

61 93 44 51; email account.airwortheas@airbus.com; Internet http://

www.airbus.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–2014–0574. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

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 all Airbus Model A318 series 

airplanes, Model A319 series airplanes, 

Model A320–211, –212, –214, –231, 

–232, and –233 airplanes, and Model 

A321 series airplanes. The NPRM 

published in the Federal Register on 

August 22, 2014 (79 FR 49724). The 

NPRM was prompted by a report of skin 

disbonding on a composite side shell 


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