This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

38406 

Vol. 80, No. 128 

Monday, July 6, 2015 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2466; Directorate 

Identifier 2015–CE–018–AD] 

RIN 2120–AA64 

Airworthiness Directives; Piaggio Aero 

Industries S.p.A Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Piaggio 

Aero Industries S.p.A Model P–180 

airplanes. This proposed AD results 

from 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 the need to restore the safe 

fatigue life of the bulkhead structure. 

We are issuing this proposed AD to 

require actions to address the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by August 20, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed 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/customersupport#care. You may review 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. 

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– 

2466; 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 proposed AD, 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. 

FOR FURTHER INFORMATION CONTACT: 

Mike Kiesov, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4144; fax: (816) 

329–4090; email: mike.kiesov@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–2466; Directorate Identifier 

2015–CE–018–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

regulations.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD No.: 2015– 

0071, dated: April 30, 2015 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

In 1997, Piaggio Aero Industries S.p.A 

(PAI) developed a modification of the 

forward pressurized bulkhead, published 

through PAI Service Bulletin (SB) 80–0081, 

aiming to restore the safe fatigue life of the 

bulkhead structure. 

Consequently, ENAC Italy (formerly RAI) 

issued Prescrizione di Aeronavigabilita (PA) 

97–148 to require compliance with this SB. 

After RAI PA 97–148 was issued, PAI 

issued SB 80–0081 Revision 2 to provide 

improved instructions for specific serial 

numbers. Prompted by this development, 

EASA issued AD 2010–0146 superseding PA 

97–148 and requiring accomplishment of 

instruction of PAI issued SB 80–0081 

Revision 2. 

After that AD was issued, PAI issued SB 

80–0081 Revision 3 to make the instructions 

for inspection (and, depending on findings, 

rework/reinforcement) applicable to all 

aeroplanes. 

For the reasons described above, this AD 

retains the requirements of EASA AD 2010– 

0146, which is superseded, requires 

inspection and, depending on findings, 

reinforcement of the pressurized bulkhead 

structure on extended population of 

aeroplanes. This AD also specifies that 

certain aeroplanes modified in accordance 

with SB 80–0081 up to Revision 2 need to 

be inspected and, depending on findings, 

reinforced as required by this AD. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–2466. 

Related Service Information Under 1 

CFR Part 51 

Piaggio Aero Industries S.p.A has 

issued Piaggio Aero Industries S.p.A. 

Service Bulletin 80–0081, Revision No. 

3, dated: January 20, 2015. The service 

information describes procedures for 

inspection and, depending on findings, 

rework/reinforcement of the bulkhead. 

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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Federal Register / Vol. 80, No. 128 / Monday, July 6, 2015 / Proposed Rules 38407 

identified in the ADDRESSES section of 

this NPRM. 

FAA’s Determination and Requirements 

of the Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 28 products of U.S. registry. 

We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators to be $2,380, or $85 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 88 work-hours and require parts 

costing $30,000, for a cost of $37,480 

per product. We have no way of 

determining the number of products 

that may need these actions. 

According to the manufacturer, some 

of the costs of this proposed 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 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed regulation: 

(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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 AD: 

Piaggio Aero Industries S.p.A: Docket No. 

FAA–2015–2466; Directorate Identifier 

2015–CE–018–AD. 

(a) Comments Due Date 

We must receive comments by August 20, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Piaggio Aero Industries 

S.p.A P–180 Model P–180 airplanes, serial 

numbers (S/N) 1004 through 1033, 

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 the need to 

restore the safe fatigue life of the bulkhead 

structure. We are issuing this AD to correct 

the safe fatigue life of the airplane. 

(f) Actions and Compliance 

(1) Unless already done, do the actions in 

paragraphs (f)(2) through (f)(4) of this AD at 

whichever of the following compliance times 

occurs later: 

(i) Within 1,500 hours time-in-service (TIS) 

after the effective date of this AD, but not to 

exceed 6,000 hours total hours TIS on the 

airplane; or 

(ii) Within 200 hours TIS after the effective 

date of this AD or 6 months after the effective 

date of this AD, whichever occurs first. 

(2) Inspect (visually or using a standard 

endoscope) the forward pressurized bulkhead 

to verify presence of bulkhead reinforcement 

following Part A1 of the Accomplishment 

Instructions of Piaggio Aero Industries S.p.A. 

Service Bulletin 80–0081, Revision No. 3, 

dated: January 20, 2015. 

(i) If the inspection results indicate that the 

reinforcements are properly installed, 

ascertain (visually or by means of standard 

endoscope equipment) that there are no 

cracks or defects. If cracks or defects are 

identified, before further flight, repair using 

instructions from Piaggio Aero Industries as 

identified in Service Letter 80–0097. 

(ii) If the inspection results indicate that 

the reinforcements are not installed, reinforce 

the forward pressurized bulkhead following 

Part A2 of the Accomplishment Instructions 

of Piaggio Aero Industries S.p.A. Service 

Bulletin 80–0081, Revision No. 3, dated: 

January 20, 2015. 

(3) Modify the forward pressurized 

bulkhead following Part C of the 

Accomplishment Instructions of Piaggio Aero 

Industries S.p.A. Service Bulletin 80–0081, 

Revision No. 3, dated: January 20, 2015. 

(4) This AD allows credit for the actions 

required in paragraphs (f)(2)(ii) and (f)(3) of 

this AD if done before the effective date of 

this AD following the instructions of Piaggio 

Aero Industries S.p.A. Service Bulletin 80– 

0081, Original Issue, dated: April 28, 1997; 

Piaggio Aero Industries S.p.A. Service 

Bulletin 80–0081, Revision No. 1, dated: May 

11, 2010; or Piaggio Aero Industries S.p.A. 

Service Bulletin 80–0081, Revision No. 2, 

dated: July 19, 2010. 

(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: Mike Kiesov, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4144; fax: (816) 329– 

4090; email: mike.kiesov@faa.gov. Before 

using any approved AMOC on any airplane 


Lhorne on DSK7TPTVN1PROD with PROPOSALS
38408 Federal Register / Vol. 80, No. 128 / Monday, July 6, 2015 / Proposed Rules 

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 European Aviation Safety 

Agency (EASA) AD No.: 2015–0071, dated 

April 30, 2015; Piaggio Aero Industries S.p.A. 

Service Bulletin 80–0081, Original Issue, 

dated: April 28, 1997; Piaggio Aero Industries 

S.p.A. Service Bulletin 80–0081, Revision 

No. 1, dated: May 11, 2010; or Piaggio Aero 

Industries S.p.A. Service Bulletin 80–0081, 

Revision No. 2, dated: July 19, 2010, for 

related information. You may examine the 

MCAI on the Internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2015–2466. For 

service information related to 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 review 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. 

Issued in Kansas City, Missouri, on June 

25, 2015. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2015–16293 Filed 7–2–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2456; Directorate 

Identifier 2015–NM–032–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all The 

Boeing Company Model 767 airplanes. 

This proposed AD was prompted by 

reports of cracking at a central part of 

the structure. This proposed AD would 

require repetitive inspections of the skin 

hidden by the upper and lower splice 

fittings on both sides of the fuselage, 

and corrective action if necessary. We 

are proposing this AD to detect and 

correct fatigue cracking of the hidden 

fuselage skin and cracking, corrosion, 

and other damage to the splice fittings 

and adjacent visible fuselage skin and 

structure that could lead to loss of a 

primary load path between the fuselage 

and the wing box, and consequent 

reduced structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by August 20, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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– 

2456. 

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– 

2456; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–2456; Directorate Identifier 2015– 

NM–032–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

While replacing a cracked underwing 

longeron fitting, a crack indication was 

found in the STA 786 ring chord at the 

tension bolt hole common to the wing 

front spar lower chord and the internal 

bathtub fittings. There were two similar 

reports of these findings from two 

separate operators. The airplanes in 

these reports had 14,367 and 18,354 

flight cycles and 90,389 and 96,826 

flight hours, respectively. The current 

inspections in the Model 767 

Maintenance Planning Document are 

not sufficient to detect any possible 

fuselage skin crack in the area adjacent 

to the ring chord at STA 786 before the 

crack extends to a critical length. The 

fuselage skin in this area is hidden 

between the splice fittings on the 

external side of the fuselage and the 

bathtub fittings on the internal side. 

This condition, if not corrected, could 

result in loss of a primary load path 

between the fuselage and the wing box, 

and consequent reduced structural 

integrity of the airplane. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 767–53A0263, dated January 


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