Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations 1489 

(m) 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: 

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. 

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

AMOC-REQUESTS@faa.gov. 

(i) 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. 

(ii) AMOCs approved previously for AD 

2013–13–04, Amendment 39–17492 (78 FR 

41286, July 10, 2013) are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0202, dated 

September 5, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-0678-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD is available at the addresses specified 

in paragraphs (o)(5) and (o)(6) of this AD. 

(o) 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. 

(3) The following service information was 

approved for IBR on February 17, 2016. 

(i) Airbus Service Bulletin A320–32–1346, 

Revision 07, dated February 10, 2015, 

including Appendices 01 and 02, dated 

February 10, 2015. 

(ii) Task 32.30.00.17, ‘‘Functional Check of 

LGCIU Power Supply Relays,’’ of Section C– 

32 of Section C, Systems and Powerplant, of 

the Airbus A318/A319/A320/A321 

Maintenance Review Board Report, Revision 

18, dated March 2013. 

(4) The following service information was 

approved for IBR on August 14, 2013 (78 FR 

41286, July 10, 2013). 

(i) Airbus Service Bulletin A320–32–1346, 

Revision 04, including Appendices 01 and 

02, dated April 22, 2011. 

(ii) Airbus Service Bulletin A320–32–1349, 

Revision 03, including Appendix 1, dated 

October 5, 2011. 

(5) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 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.airworth-eas@airbus.com; Internet 

http://www.airbus.com. 

(6) 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. 

(7) 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 

December 31, 2015. 

Philip Forde, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00014 Filed 1–12–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1984; Directorate 

Identifier 2015–NM–022–AD; Amendment 

39–18363; AD 2016–01–04] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2005–01– 

09, which applied to certain The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747– 

400D, 747–400F, and 747SR series 

airplanes. AD 2005–01–09 required a 

one-time detailed inspection for 

discrepancies of the frame web and 

inner chords on the forward edge frame 

of the number 5 main entry door cutout, 

and corrective action if necessary. This 

new AD adds repetitive high frequency 

eddy current (HFEC) inspections for 

cracking of the frame inner chords 

(forward and aft), and corrective action 

if necessary. This AD was prompted by 

additional cracking found in the same 

area after completion of the one-time 

detailed inspection. We are issuing this 

AD to detect and correct discrepancies 

of the frame web and inner chords, 

which could result in cracking, 

subsequent severing of the frame, and 

consequent rapid depressurization of 

the airplane. 

DATES: This AD is effective February 17, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 17, 2016. 

ADDRESSES: For 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. 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– 

1984. 

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– 

1984; 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: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6428; fax: 

425–917–6590; email: 

nathan.p.weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 


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1490 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2005–01–09, 

Amendment 39–13933 (70 FR 1340, 

January 7, 2005). AD 2005–01–09 

applied to certain The Boeing Company 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747–400, 747–400D, 747– 

400F, and 747SR series airplanes. The 

NPRM published in the Federal 

Register on June 24, 2015 (80 FR 36255) 

(‘‘the NPRM’’). The NPRM was 

prompted by additional cracking found 

in the same area after completion of the 

one-time detailed inspection. The 

NPRM proposed to continue to require 

a one-time detailed inspection for 

discrepancies of the frame web and 

inner chords on the forward edge frame 

of the number 5 main entry door cutout, 

and corrective action if necessary. The 

NPRM also proposed to require 

repetitive HFEC inspections for cracking 

of the frame inner chords (forward and 

aft), and corrective action if necessary. 

We are issuing this AD to detect and 

correct discrepancies of the frame web 

and inner chords, which could result in 

cracking, subsequent severing of the 

frame, and consequent rapid 

depressurization of the airplane. 

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. United 

Airlines concurred with the NPRM. 

Request for Credit for Accomplishing 

Certain Inspections Required by AD 

2013–17–08, Amendment 39–17572 (78 

FR 57053, September 17, 2013) (‘‘AD 

2013–17–08’’) 

UPS asked that credit be included in 

the proposed AD (80 FR 36255, June 24, 

2015) for accomplishing the inspections 

required by AD 2013–17–08. UPS stated 

that paragraph (g) of the proposed AD 

would require accomplishing the same 

inspections that are required by AD 

2013–17–08. UPS added that the 

proposed AD has a lower threshold for 

accomplishing the inspections than that 

in AD 2013–17–08. UPS noted that 

Boeing confirmed that these inspections 

are duplicated and stated that a revision 

of the service information may be 

forthcoming to provide clarification. 

We agree with the commenter that 

accomplishing the inspections required 

by AD 2013–17–08 before the effective 

date of this AD is acceptable for 

compliance with the inspections 

required by this AD. We had already 

included credit for accomplishing the 

inspections required by AD 2013–17–08 

in paragraph (i)(2) of the proposed AD. 

However, since the compliance time 

in AD 2013–17–08 is later than the 

compliance time required by this AD, 

we have not given credit for inspections 

that will be done for AD 2013–17–08 on 

or after the effective date of this AD. 

Operators may apply for approval of an 

AMOC in accordance with the 

provisions specified in paragraph (j) of 

this AD, by submitting data 

substantiating that the request would 

provide an acceptable level of safety. 

Therefore, we have made no further 

change to this AD. 

Request To Include Terminating Action 

UPS also recommended adding a 

sentence to paragraph (h) of the 

proposed AD to terminate the repetitive 

inspections required by AD 2013–17– 

08, after accomplishment of the initial 

inspections required by the proposed 

AD. 

We do not agree to specify that the 

actions required by paragraph (h) of this 

AD terminate the repetitive inspections 

required by AD 2013–17–08, because 

those inspections are more extensive 

than the inspections in this AD. 

However, affected operators who wish 

to terminate the repetitive inspections 

required by AD 2013–17–08 may apply 

for approval of an AMOC in accordance 

with the provisions specified in 

paragraph (j) of this AD, by submitting 

data substantiating that the request 

would provide an acceptable level of 

safety. We have not changed this AD in 

this regard. 

Request To Correct Typographical 

Error 

Boeing asked that a typographical 

error in the ‘‘Related AD’’ section of the 

proposed AD be corrected. Boeing stated 

that the description of the inspection 

area in AD 2013–17–08 of the frame 

segment should be changed from 

‘‘between 16 and 31’’ to ‘‘between 15 

and 31.’’ Boeing noted that this is a 

typographical error. 

We agree that there is a typographical 

error in the ‘‘Related AD’’ section of the 

proposed AD, as noted by the 

commenter. That section should specify 

‘‘the frame segment between 15 and 31’’; 

however, since that section of the 

preamble does not reappear in the final 

rule, no change to this AD is necessary 

in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, with 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. 

Related Service Information Under 1 

CFR Part 51 

We reviewed and approved Boeing 

Alert Service Bulletin 747–53A2494, 

Revision 1, dated January 9, 2015. The 

service information describes 

procedures for a one-time detailed 

inspection and repetitive surface HFEC 

inspections of the Station 2231 frame 

inner chords (forward and aft), and 

repair of discrepancies. 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 174 

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 

Detailed inspection .................. 2 work-hours × $85 per hour = 

$170.

$0 $170 ........................................ $29,580. 

HFEC inspections .................... 4 work-hours × $85 per hour = 

$340.

0 $340 per inspection cycle ....... $59,160 per inspection cycle. 


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Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations 1491 

We have received no definitive data 

that will enable us to provide a cost 

estimate 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 

We have 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 

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 

removing Airworthiness Directive (AD) 

2005–01–09, Amendment 39–13933 (70 

FR 1340, January 7, 2005), and adding 

the following new AD: 

2016–01–04 The Boeing Company: 

Amendment 39–18363; Docket No. 

FAA–2015–1984; Directorate Identifier 

2015–NM–022–AD. 

(a) Effective Date 

This AD is effective February 17, 2016. 

(b) Affected ADs 

This AD replaces AD 2005–01–09, 

Amendment 39–13933 (70 FR 1340, January 

7, 2005) (‘‘AD 2005–01–09’’). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, –100B, 747–100B SUD, 747– 

200B, 747–200C, 747–200F, 747–300, 747– 

400, 747–400D, 747–400F, and 747SR series 

airplanes; certificated in any category; as 

identified in Boeing Alert Service Bulletin 

747–53A2494, Revision 1, dated January 9, 

2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

additional cracking found in the same area 

after completion of the one-time detailed 

inspection. We are issuing this AD to detect 

and correct discrepancies of the frame web 

and inner chords, which could result in 

cracking, subsequent severing of the frame, 

and consequent rapid depressurization of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections 

Do the applicable actions specified in 

paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of 

this AD, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2494, Revision 1, 

dated January 9, 2015, except as required by 

paragraph (h)(2) of this AD. 

(1) At the applicable time specified in 

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

Alert Service Bulletin 747–53A2494, 

Revision 1, dated January 9, 2015, except as 

required by paragraph (h)(1) of this AD: Do 

a detailed inspection for nicks, scratches, or 

gouges of the Station 2231 frame inner 

chords, forward and aft, at stringer 26 at the 

edge and side of the inner chords. 

(2) At the applicable time specified in 

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

Alert Service Bulletin 747–53A2494, 

Revision 1, dated January 9, 2015, except as 

required by paragraph (h)(1) of this AD: Do 

a surface high frequency eddy current (HFEC) 

inspection for cracks of the frame inner 

chords, forward and aft. 

(3) Based on the findings from the 

inspections specified in paragraphs (g)(1) and 

(g)(2) of this AD, do all applicable corrective 

actions, before further flight. 

(4) Repeat the HFEC inspection specified 

in paragraph (g)(2) of this AD at the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2494, Revision 1, dated 

January 9, 2015. 

(h) Exceptions to Service Bulletin 

Specifications 

(1) Where Boeing Alert Service Bulletin 

747–53A2494, Revision 1, dated January 9, 

2015, specifies a compliance time ‘‘after the 

release of Revision 1 of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2494, Revision 1, dated January 9, 

2015, specifies to contact Boeing for repair 

instructions: Before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (j) of 

this AD. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for 

inspections required by paragraph (g)(1) of 

this AD, if those inspections were performed 

before the effective date of this AD using 

Boeing Alert Service Bulletin 747–53A2494, 

dated September 18, 2003, which was 

incorporated by reference in AD 2005–01–09. 

(2) This paragraph provides credit for 

inspections required by paragraphs (g)(1) and 

(g)(2) of this AD, if those inspections were 

performed before the effective date of this AD 

using Boeing Alert Service Bulletin 747– 

53A2450, Revision 7, dated November 2, 

2011, which was incorporated by reference in 

AD 2013–17–08, Amendment 39–17572 (78 

FR 57053, September 17, 2013). 

(j) 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 (k) 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 


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1492 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations 

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) AMOCs approved for AD 2005–01–09 

are approved as AMOCs for the 

corresponding provisions of paragraph (g)(1) 

of this AD. 

(k) Related Information 

For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6428; fax: 425–917– 

6590; email: nathan.p.weigand@faa.gov. 

(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 the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 747– 

53A2494, Revision 1, dated January 9, 2015. 

(ii) Reserved. 

(3) For 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 

December 28, 2015. 

Philip Forde, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00011 Filed 1–12–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8695; Directorate 

Identifier 2015–SW–042–AD; Amendment 

39–18365; AD 2016–01–06] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Agusta 

S.p.A. (Agusta) Model AB139 and 

AW139 helicopters. This AD requires 

inspecting each full ice protection 

system tail rotor slip ring (slip ring) for 

chatter marks, witness marks, or 

scoring, and determining the depth of 

each mounting hole. Based on the 

findings from the inspection, this AD 

requires either re-identifying the slip 

ring or replacing the slip ring. This AD 

is prompted by two incidents of the slip 

ring body separating from the 

supporting flange due to improper 

torque. These actions are intended to 

prevent separation of the mounting 

flange from the slip ring body and 

subsequent loss of control of the 

helicopter. 

DATES: This AD becomes effective 

January 28, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of January 28, 2016. 

We must receive comments on this 

AD by March 14, 2016. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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– 

8695; 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, the European Aviation 

Safety Agency (EASA) AD, any 

incorporated by reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

For service information identified in 

this final rule, contact AgustaWestland, 

Product Support Engineering, Via del 

Gregge, 100, 21015 Lonate Pozzolo (VA) 

Italy, ATTN: Maurizio D’Angelo; 

telephone 39–0331–664757; fax 39– 

0331–664680; or at http://

www.agustawestland.com/technicalbulletins; and Moog Inc., Components 

Group, Blacksburg Operations, 1213 

North Main St., Blacksburg, Virginia 

24606–3127, telephone (540) 552–3011, 

or at www.moog.com. You may review 

the referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy, Room 6N–321, Fort Worth, TX 

76177. 

FOR FURTHER INFORMATION CONTACT: 

Martin R. Crane, Aviation Safety 

Engineer, Safety Management Group, 

Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy, Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

martin.r.crane@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. We will file 

in the docket all comments that we 

receive, as well as a report summarizing 

each substantive public contact with 


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