58346 Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2015–19–13 Bombardier, Inc.: Amendment 

39–18275. Docket No. FAA–2015–0494; 

Directorate Identifier 2014–NM–160–AD. 

(a) Effective Date 

This AD becomes effective November 3, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–400, –401, and –402 airplanes, 

certificated in any category, serial numbers 

4001 and 4003 through 4453 inclusive with 

an outboard spoiler power control unit (PCU) 

having part number 390700–1007 installed in 

the outboard position. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by reports of 

inadvertent deployment of a single outboard 

spoiler during flight. We are issuing this AD 

to prevent leakage of the piston head seal and 

piston rod seals of the outboard spoiler PCUs, 

which could result in inadvertent spoiler 

deployment and reduced controllability of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement of PCUs for the Outboard 

Spoilers 

Within 6,000 flight hours or 36 months 

after the effective date of this AD, whichever 

occurs first: Replace the outboard spoiler 

PCUs with upgraded PCUs having redesigned seals, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–63, dated October 17, 

2013. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

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. 

(2) Contacting the Manufacturer: 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, New York ACO, ANE–170, 

FAA; or Transport Canada Civil Aviation 

(TCCA); or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(i) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–22, dated 

July 16, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

#!documentDetail;D=FAA-2015-0494-0002. 

(j) 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. 

(i) Bombardier Service Bulletin 84–27–63, 

dated October 17, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., Q Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.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 

September 16, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–24252 Filed 9–28–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0929; Directorate 

Identifier 2014–NM–118–AD; Amendment 

39–18274; AD 2015–19–12] 

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 767 

airplanes. This AD was prompted by 

reports that six fasteners may not have 

been installed in the left and right 

stringer 37 (S–37) between body stations 

(BS) 428 and 431 lap splices on certain 

airplanes. This AD requires a general 

visual inspection of S–37 lap splices for 

missing fasteners, and all applicable 

related investigative and corrective 

actions. We are issuing this AD to detect 

and correct missing fasteners, which 

could result in cracks in the fuselage 

skin that could adversely affect the 

structural integrity of the airplane. 

DATES: This AD is effective November 3, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 3, 2015. 

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–2014– 

0929. 

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–2014– 

0929; 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 


asabaliauskas on DSK5VPTVN1PROD with RULES
Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations 58347 

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: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6447; 

fax: 425–917–6590; email: 

Wayne.Lockett@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 767 airplanes. The NPRM 

published in the Federal Register on 

December 29, 2014 (79 FR 77970). The 

NPRM was prompted by reports that six 

fasteners may not have been installed in 

the left and right S–37 between BS 428 

and 431 lap splices on certain airplanes. 

The NPRM proposed to require a 

general visual inspection of S–37 lap 

splices for missing fasteners, and all 

applicable related investigative and 

corrective actions. We are issuing this 

AD to detect and correct missing 

fasteners, which could result in cracks 

in the fuselage skin that could adversely 

affect the structural integrity 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 (79 FR 77970, 

December 29, 2014) and the FAA’s 

response to each comment. 

Support for the NPRM (79 FR 77970, 

December 29, 2014) 

Boeing and Debra Abdou supported 

the NPRM (79 FR 77970, December 29, 

2014). FedEx Express explained that the 

NPRM will not impact them. United 

Airlines stated that it has no comment 

on the NPRM. 

Request for Credit for Previous Actions 

United Parcel Service (UPS) requested 

that we revise the NPRM (79 FR 77970, 

December 29, 2014), to clarify that no 

further actions are required for airplanes 

that have previously accomplished 

inspections and corrective actions as 

specified in Boeing Message TBC–UPS– 

13–0004–01B (Service Request 1– 

2412169241), dated February 1, 2013. 

UPS explained that, prior to the 

release of Boeing Alert Service Bulletin 

767–53A0251, dated August 7, 2013, 

Boeing had released Boeing Fleet Team 

Digest article 767–FTD–53–12003, dated 

September 21, 2012; and Boeing 

Message TBC–UPS–13–0004–01B 

(Service Request 1–2412169241), dated 

February 1, 2013; to address the 

discrepant condition and provide 

applicable corrective actions. UPS 

stated that it has previously 

accomplished inspections and 

corrective actions on all affected UPS 

Model 767–300F series airplanes in 

accordance with Boeing Fleet Team 

Digest article 767–FTD–53–12003 dated 

September 21, 2012, and Boeing 

Message TBC–UPS–13–0004–01B 

(Service Request 1–2412169241), dated 

February 1, 2013. Per Boeing Message 

TBC–UPS–13–0004–01B (Service 

Request 1–2412169241), dated February 

1, 2013, the following corrective actions 

are to be accomplished prior to further 

flight if the affected fasteners are found 

missing: 

• Remove the center row and adjacent 

fasteners around the missing fastener 

locations. 

• Perform open-hole high frequency 

eddy current (HFEC) inspection for 

damages. 

• If no damage is found, install 

BACR15FV6KE* rivets per the Boeing 

installation drawing. 

• If damage is found, repair per the 

service repair manual section defined in 

the future service bulletin. 

UPS reasoned that, as indicated in 

Boeing Message TBC–UPS–13–0004– 

01B (Service Request 1–2412169241), 

dated February 1, 2013, the additional 

detailed inspection shown in Figure 2, 

Step 1, of Boeing Alert Service Bulletin 

767–53A0251, dated August 7, 2013, is 

not required to detect damages resulting 

from the discrepant condition. UPS 

expressed that, as supported by Boeing 

Message TBC–UPS–13–0004–01B 

(Service Request 1–2412169241), dated 

February 1, 2013, the open-hole HFEC 

inspection is sufficient for detecting and 

eliminating damage resulting from the 

identified unsafe condition. UPS 

pointed out that standard maintenance 

procedures ensure that the external and 

internal areas accessed and disturbed 

during accomplishment of the repair are 

restored to normal configuration. 

Furthermore, UPS explained that 

supplemental internal and external 

inspections of the affected area are 

accomplished per UPS maintenance 

program as specified in Boeing 

Maintenance Planning Document Items 

53–460–00, 53–648–00, 53–800–00, and 

53–820–00. 

We disagree to provide credit for 

certain actions required by this AD if 

those actions were performed before the 

effective date of this AD using Boeing 

Message TBC–UPS–13–0004–01B 

(Service Request 1–2412169241) dated 

February 1, 2013. It is possible that 

individual instructions provided to the 

specific operator via Boeing Message 

TBC–UPS–13–0004–01B (Service 

Request 1–2412169241), dated February 

1, 2013, may have different instructions 

than those specified in the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 767–53A0251, 

dated August 7, 2013. However, under 

the provisions of paragraph (i) of this 

AD, we will consider requests for 

approval of credit for certain actions if 

sufficient data are submitted to 

substantiate that the change would 

provide an acceptable level of safety. 

We have made no changes to this AD in 

this regard. 

Effect of Winglets on AD 

Aviation Partners Boeing stated that 

accomplishing the supplemental type 

certificate (STC) ST01920SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

59027f43b9a7486e86257b1d006591ee/

$FILE/ST01920SE.pdf) does not affect 

the actions specified in the NPRM (79 

FR 77970, December 29, 2014). We 

concur with the commenter. We have 

redesignated paragraph (c) of the 

proposed AD as paragraph (c)(1) and 

added new paragraph (c)(2) to this AD 

to state that installation of STC 

ST01920SE does not affect the ability to 

accomplish the actions required by this 

final rule. Therefore, for airplanes on 

which STC ST01920SE is installed, a 

‘‘change in product’’ alternative method 

of compliance (AMOC) approval request 

is not necessary to comply with the 

requirements of 14 CFR 39.17. 

Related Service Information Under 1 

CFR Part 51 

Boeing has issued Boeing Alert 

Service Bulletin 767–53A0251, dated 

August 7, 2013. The service information 

describes procedures for an external 

general visual inspection of the S–37 lap 

splice for missing fasteners, detailed 

and open-hole inspections of the skin 

for any crack, corrosion, or other 

discrepancy; determining if the crack, 

corrosion, or other discrepancy is 

within the repair limits, and repairing. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 


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58348 Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations 

identified in the ADDRESSES section of 

this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

77970, December 29, 2014) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 77970, 

December 29, 2014). 

Costs of Compliance 

We estimate that this AD affects 23 

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 

General visual inspection ................................ 1 work-hour × $85 per hour = $85 ................. $0 $85 $1,955 

We estimate the following costs to do 

any necessary inspections/installations 

that would be required based on the 

results of the required inspection. We 

have no way of determining the number 

of aircraft that might need these 

inspections/installations: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Detailed and HFEC inspections and fastener installation.13 work-hours × $85 per hour = $1,105 ...................... * $1,105 

* All parts that are required are supplied by the operator. This cost is minimal, and we have no way to determine what the operators would pay 

for these parts. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the repairs specified in this 

AD. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2015–19–12 The Boeing Company: 

Amendment 39–18274; Docket No. 

FAA–2014–0929; Directorate Identifier 

2014–NM–118–AD. 

(a) Effective Date 

This AD is effective November 3, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 767–200, –300, –300F, and 

–400ER series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 767–53A0251, dated August 

7, 2013. 

(2) Installation of Supplemental Type 

Certificate (STC) [ST01920SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/59027f43b9a7486e86257b

1d00659v1ee/$FILE/ST01920SE.pdf) does 

not affect the ability to accomplish the 

actions required by this AD. Therefore, for 

airplanes on which STC ST01920SE is 

installed, a ‘‘change in product’’ alternative 

method of compliance (AMOC) approval 


asabaliauskas on DSK5VPTVN1PROD with RULES
Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations 58349 

request is not necessary to comply with the 

requirements of 14 CFR 39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports that six 

fasteners may not have been installed in the 

left and right stringer 37 (S–37) between body 

stations (BS) 428 and 431 lap splices on 

certain airplanes. We are issuing this AD to 

detect and correct missing fasteners, which 

could result in cracks in the fuselage skin 

that could adversely affect the structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections, Related Investigative 

Actions, and Corrective Actions 

Except as provided by paragraph (h)(2) of 

this AD, at the applicable time specified in 

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

Alert Service Bulletin 767–53A0251, dated 

August 7, 2013: Do an external general visual 

inspection of the S–37 lap splice for missing 

fasteners, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–53A0251, dated August 7, 2013, except 

as provided by paragraph (h)(1) of this AD. 

Do all applicable related investigative and 

corrective actions before further flight. 

(h) Exceptions to Service Information 

Specifications 

(1) Although Boeing Alert Service Bulletin 

767–53A0251, dated August 7, 2013, 

specifies to contact Boeing for repair 

instructions, and specifies that action as 

‘‘RC’’ (Required for Compliance), this AD 

requires repair before further flight using a 

method approved in accordance with the 

procedures specified in paragraph (i)(1) of 

this AD. 

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

Boeing Alert Service Bulletin 767–53A0251, 

dated August 7, 2013, 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. 

(i) 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 (j) 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 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and the 

approval must specifically refer to this AD. 

(4) Except as required by paragraph (h)(1) 

of this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (i)(4)(i) and (i)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(j) Related Information 

For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6447; fax: 425– 

917–6590; email: Wayne.Lockett@faa.gov. 

(k) 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 767– 

53A0251, dated August 7, 2013. 

(ii) Reserved. 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https://

www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

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

Issued in Renton, Washington, on 

September 11, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–24146 Filed 9–28–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2466; Directorate 

Identifier 2015–CE–018–AD; Amendment 

39–18273; AD 2015–19–11] 

RIN 2120–AA64 

Airworthiness Directives; Piaggio Aero 

Industries S.p.A. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Piaggio 

Aero Industries S.p.A. Model P–180 

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 the 

need to restore the safe fatigue life of the 

bulkhead structure. We are issuing this 

AD to require actions to address the 

unsafe condition on these products. 

DATES: This AD is effective November 3, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publication listed in the AD 

as of November 3, 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– 

2466; or in person at 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 service information identified in 

this AD, contact PIAGGIO AERO 

INDUSTRIES S.p.A, Airworthiness 

Office, Viale Generale Disegna, 

1 - 17038 Villanova d’Albenga, Savona, 

Italy; telephone: +39 010 6481800; fax: 

+39 010 6481374; email: 

technicalsupport@piaggioaerospace.it; 

Internet: www.piaggioaerospace.it/en/

customer-support#care. You may view 

this referenced service information at 


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