68172 Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0778 Directorate 

Identifier 2010–CE–034–AD; Amendment 

39–16490; AD 2010–23–01] 

RIN 2120–AA64 

Airworthiness Directives; Piaggio Aero 

Industries S.p.A. Model PIAGGIO 

P–180 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. 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: 

Some cases of corrosion were detected in 

the interface between the elevator hinges 

fittings (metallic) and the horizontal 

stabilizer (carbon fibre); investigation 

identified the cause in galvanic corrosion 

between dissimilar materials. 

If left uncorrected, this situation could lead 

to a structural failure of the elevator, which 

could result in possible loss of control of the 

aeroplane. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

December 10, 2010. 

On December 10, 2010, the Director of 

the Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov 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., Via Cibrario, 4–16154 Genoa, 

Italy; phone: +39 010 6481 800; fax: +39 

010 6481 374; e-mail: 

tech.support@piaggioaero.it; Internet: 

http://www.piaggioaero.com. You may 

review copies of the 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. 

FOR FURTHER INFORMATION CONTACT: 

Sarjapur Nagarajan, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4145; fax: (816) 329–4090; e-mail: 

sarjapur.nagarajan@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on August 9, 2010 (75 FR 

47734). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Some cases of corrosion were detected in 

the interface between the elevator hinges 

fittings (metallic) and the horizontal 

stabilizer (carbon fibre); investigation 

identified the cause in galvanic corrosion 

between dissimilar materials. 

If left uncorrected, this situation could lead 

to a structural failure of the elevator, which 

could result in possible loss of control of the 

aeroplane. 

This AD requires: 

(1) Inspection of the hinges fittings for 

corrosion and of the stabilizer for 

delamination; 

(2) Repair of the stabilizer, if necessary; 

(3) Replacement of the fittings, if corroded; 

(4) Improvement of fittings installation; 

(5) Installation of aluminum strips in the 

stabilizer to improve bonding, in accordance 

with Piaggio Aero Industries (PAI) Service 

Bulletin (SB) 80–0262 Revision 2. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 96 products of U.S. registry. 

We also estimate that it would take 

about 9 work-hours 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 $73,440, or $765 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 32 work-hours and require parts 

costing $11,000, for a cost of $13,720 

per product. We have no way of 

determining the number of products 

that may need these actions. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

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Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations 68173 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD Docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains the NPRM, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2010–23–01 Piaggio Aero Industries S.p.A.: 

Amendment 39–16490; Docket No. 

FAA–2010–0778; Directorate Identifier 

2010–CE–034–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective December 10, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model PIAGGIO P– 

180 airplanes, serial numbers 1002 and 1004 

through 1191, certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 55: Stabilizers. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Some cases of corrosion were detected in 

the interface between the elevator hinges 

fittings (metallic) and the horizontal 

stabilizer (carbon fibre); investigation 

identified the cause in galvanic corrosion 

between dissimilar materials. 

If left uncorrected, this situation could lead 

to a structural failure of the elevator, which 

could result in possible loss of control of the 

aeroplane. 

This AD requires: 

(1) Inspection of the hinges fittings for 

corrosion and of the stabilizer for 

delamination; 

(2) Repair of the stabilizer, if necessary; 

(3) Replacement of the fittings, if corroded; 

(4) Improvement of fittings installation; 

(5) Installation of aluminum strips in the 

stabilizer to improve bonding, in accordance 

with Piaggio Aero Industries (PAI) Service 

Bulletin (SB) 80–0262 Revision 2. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within the next 1,500 hours time-inservice (TIS) after December 10, 2010 (the 

effective date of this AD) or within 4 years 

after December 10, 2010 (the effective date of 

this AD), whichever occurs first, do the 

following: 

(i) Remove the left-hand (LH) and the righthand (RH) elevators and do all of the 

inspections and corrective actions following 

the Accomplishment Instructions in Parts A, 

B, C, D, and E of PIAGGIO AERO 

INDUSTRIES S.p.A. Service Bulletin 

(MANDATORY) N.: SB–80–0262, Revision 2, 

dated March 17, 2010. 

(ii) Reinstall the LH and RH elevators and 

do the final checks following the 

Accomplishment Instructions, Part F, of 

PIAGGIO AERO INDUSTRIES S.p.A. Service 

Bulletin (MANDATORY) N.: SB–80–0262 

Revision 2, dated March 17, 2010. 

(2) We will allow ‘‘unless already done’’ 

credit for inspections and corrective actions 

already done, before the effective date of this 

AD, following PIAGGIO AERO INDUSTRIES 

S.p.A. Service Bulletins (MANDATORY) N.: 

SB–80–0262, original issue dated September 

24, 2009; or Revision 1 dated December 23, 

2009, for compliance with the requirements 

of this AD. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) 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: Sarjapur Nagarajan, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4145; fax: (816) 

329–4090; e-mail: 

sarjapur.nagarajan@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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(h) Refer to MCAI EASA AD No.: 2010– 

0124 (Correction: June 22, 2010), dated June 

22, 2010; and PIAGGIO AERO INDUSTRIES 

S.p.A. Service Bulletin (MANDATORY) N.: 

SB–80–0262, Revision 2, dated March 17, 

2010, for related information. 

Material Incorporated by Reference 

(i) You must use PIAGGIO AERO 

INDUSTRIES S.p.A. Service Bulletin 

(MANDATORY) N.: SB–80–0262, Revision 2, 

dated March 17, 2010, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Piaggio Aero Industries 

S.p.a., Via Cibrario, 4–16154 Genoa, Italy; 

phone: +39 010 6481 800; fax: +39 010 6481 

374; e-mail: tech.support@piaggioaero.it; 

Internet: http://www.piaggioaero.com. 

(3) You may review copies of the 

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. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

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68174 Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations 

Issued in Kansas City, Missouri, on 

October 21, 2010. 

Christina L. Marsh, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–27456 Filed 11–4–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1041; Directorate 

Identifier 2010–NM–198–AD; Amendment 

39–16493; AD 2010–23–04] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8–400 Series 

Airplanes 

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 the 

products listed above. This 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: 

Several reports have been received of 

cracked nacelle attachment fittings. The 

preliminary investigation determined the 

cause to be stress corrosion. Stress corrosion 

cracking could compromise the structural 

integrity of the nacelle attachment fitting and 

could adversely affect the safe landing of the 

aeroplane. 

Failure of the fitting could result in 

collapse of the landing gear. This AD 

requires actions that are intended to 

address the unsafe condition described 

in the MCAI. 

DATES: This AD becomes effective 

November 22, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 22, 2010. 

We must receive comments on this 

AD by December 20, 2010. 

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 W12–40, 1200 New Jersey 

Avenue, SE., Washington, DC, 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; 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 regulatory 

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 FURTHER INFORMATION CONTACT: 

Craig Yates, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7355; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2010–30R1, 

dated September 21, 2010 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

Several reports have been received of 

cracked nacelle attachment fittings. The 

preliminary investigation determined the 

cause to be stress corrosion. Stress corrosion 

cracking could compromise the structural 

integrity of the nacelle attachment fitting and 

could adversely affect the safe landing of the 

aeroplane. 

This [Canadian] directive, as an interim, 

mandates a detailed visual inspection [for 

cracking] and conductivity check of each of 

the four (4) nacelle attachment fittings. 

Revision 1 of this [Canadian] directive is 

issued to update the aircraft serial number 

(S/N) applicability based on the latest crack 

findings and also to revise the acceptable 

conductivity values in Part I.A. In addition, 

Part II. has been added to provide 

instructions for newly affected aircraft and 

aircraft that have replaced nacelle attachment 

fittings. 

Failure of the fitting could result in 

collapse of the landing gear. Required 

actions include repetitive detailed 

inspections and replacement of the 

fittings, depending on inspection 

findings. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Bombardier has issued Service 

Bulletin 84–54–14, Revision J, dated 

September 17, 2010. For certain 

airplanes, this service bulletin describes 

procedures for a conductivity inspection 

and a repetitive detailed inspection for 

cracking of the nacelle attachment 

fittings. If the inspections find cracking, 

this service bulletin specifies 

replacement of the fitting, or if the 

inspection finds certain conductivity 

results, a daily repetitive detailed 

inspection until replacement of the 

fitting is accomplished. For certain 

other airplanes, this service bulletin 

describes repetitive detailed inspections 

for cracking of the nacelle attachment 

fittings and replacement of the fitting if 

any cracking is found. For all airplanes, 

this service bulletin specifies that 

replacement of the fitting extends the 

compliance time for the first repetitive 

detailed inspection on that fitting. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This 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 the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between the AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a Note within the AD. 

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