Federal Register / Vol. 76, No. 170 / Thursday, September 1, 2011 / Proposed Rules 54403 

paragraphs (m)(1), (m)(2), and (m)(3) of this 

AD are met. 

(1) The repair is installed after the 

applicable date specified in paragraph 

(m)(1)(i) and (m)(1)(ii) of this AD. 

(i) For repairs at S–1 and S–2R between 

STA 827 and STA 847: Installed after 

September 3, 2009. 

(ii) For repairs at locations other than at S– 

1 and S–2R between STA 827 and STA 847: 

Installed after June 7, 2010. 

(2) The repair was approved by the FAA 

or by a Boeing Company Authorized 

Representative or the Boeing Commercial 

Airplanes Organization Designation 

Authorization (ODA) that has been 

authorized by the Manager, Seattle Aircraft 

Certification Office (ACO) to make such 

findings; and 

(3) The repair extends a minimum of three 

rows of fasteners on each side of the chemmill line in the circumferential direction. 

(n) Accomplishing a modification of the 

chem-milled steps at any location identified 

in Boeing Alert Service Bulletin 737– 

53A1301, Revision 2, dated April 25, 2011, 

using a method approved in accordance with 

the procedures specified in paragraph (q)(1) 

of this AD, terminates the repetitive 

inspections required by paragraphs (g) and (j) 

of this AD for the modified area only. 

Group 26 Airplanes 

(o) For Group 26 airplanes identified in 

Boeing Alert Service Bulletin 737–53A1301, 

Revision 2, dated April 25, 2011: Within 

1,800 flight cycles after the effective date of 

this AD, accomplish applicable inspections 

and corrective action, as identified in the 

service bulletin, using a method approved in 

accordance with the procedures specified in 

paragraph (q)(1) of this AD. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(p) Actions done before the effective date 

of this AD in accordance with Boeing Alert 

Service Bulletin 737–53A1301, Revision 1, 

dated June 7, 2010, are acceptable for 

compliance with the corresponding 

requirements of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(q)(1) The Manager, Seattle 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 the 

Related Information section of this AD. 

Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@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 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. 

Related Information 

(r) For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

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

6590; e-mail: wayne.lockett@faa.gov. 

(s) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

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

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. You 

may review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on August 

25, 2011. 

Ali Bahrami, 

Manager Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–22370 Filed 8–31–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0954; Directorate 

Identifier 2011–CE–028–AD] 

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: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. 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: 

Some lock sleeves (part number (P/N) 

114146681), which were installed in some 

Main Landing Gear (MLG) actuators, had 

been incorrectly manufactured. 

If left uncorrected, this condition could 

lead to failure to lock the MLG actuator or 

to its unlock from the correct position, with 

subsequent possible damage to the aeroplane 

and injuries to occupants during landing. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by October 17, 2011. 

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; 

Via Luigi Cibrario, 4–16154 Genova– 

Italy; telephone: +39 010 6481353; fax: 

+39 010 6481881; E-mail: 

airworthiness@piaggioaero.it. 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. 

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 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; e-mail: 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. 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
54404 Federal Register / Vol. 76, No. 170 / Thursday, September 1, 2011 / Proposed Rules 

FAA–2011–0954; Directorate Identifier 

2011–CE–028–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 EASA AD No.: 

2011–0133, dated July 12, 2011 (referred 

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

an unsafe condition for the specified 

products. The MCAI states: 

Some lock sleeves (part number (P/N) 

114146681), which were installed in some 

Main Landing Gear (MLG) actuators, had 

been incorrectly manufactured. 

If left uncorrected, this condition could 

lead to failure to lock the MLG actuator or 

to its unlock from the correct position, with 

subsequent possible damage to the aeroplane 

and injuries to occupants during landing. 

This AD requires replacing defective MLG 

actuators with serviceable ones. 

Defective actuators can be repaired by the 

manufacturer and identified with the ‘‘P180– 

32–29’’ marking on the name plate. 

Relevant Service Information 

Piaggio Aero Industries S.p.A. has 

issued Mandatory Service Bulletin No. 

80–0304, dated July 9, 2010. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

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. 

Differences Between This Proposed 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 proposed 

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 

proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 102 products of U.S. registry. 

We also estimate that it would take 

about .5 work-hour per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $0 per product. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators to be $4,335, or $42.50 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 7 work-hours and require parts 

costing $64,822, for a cost of $65,417 

per product. There are a maximum of 17 

actuators that are identified by the 

manufacturer that will be required to be 

replace. We have no way of determining 

the number of affected airplanes on the 

U.S. registry that may have these 

actuators that may have to be replaced 

by 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. 

There is a warranty expiration date for 

the replacement of the actuators. The 

FAA recommends owners/operators that 

have affected main landing gear 

actuators contact the manufacturer 

immediately and replace the actuators 

under warranty. 

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); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

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–2011–0954; Directorate Identifier 

2011–CE–028–AD. 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
Federal Register / Vol. 76, No. 170 / Thursday, September 1, 2011 / Proposed Rules 54405 

Comments Due Date 

(a) We must receive comments by October 

17, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to PIAGGIO AERO 

INDUSTRIES S.p.A Model PIAGGIO P–180 

airplanes, all serial numbers, that are: 

(1) Certificated in any category; and 

(2) have installed any of the following 

main landing gear (MLG) actuators: 

(i) Messier-Dowty Part Number (P/N) 

114346003 (left hand side): with serial 

number (S/N) SA0706275, SA0706276, 

SA0706726, SA0706727, SA0706728, 

SA0706729, SA0706738, 

SA0706739,SA0707243, SA0707864, or 

SA0708072; or 

(ii) Messier-Dowty P/N 114346004 (right 

hand side): with S/N SA0703800, 

SA0703801, SA0705520, SA0706219, 

SA0706960, or SA0706961. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 32: Landing Gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Some lock sleeves (part number (P/N) 

114146681), which were installed in some 

Main Landing Gear (MLG) actuators, had 

been incorrectly manufactured. 

If left uncorrected, this condition could 

lead to failure to lock the MLG actuator or 

to its unlock from the correct position, with 

subsequent possible damage to the aeroplane 

and injuries to occupants during landing. 

This AD requires replacing defective MLG 

actuators with serviceable ones. 

Defective actuators can be repaired by the 

manufacturer and identified with the ‘‘P180– 

32–29’’ marking on the name plate. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within 25 hours time-in-service (TIS) 

after the effective date of this AD, inspect 

both installed MLG actuators to determine if 

an affected P/N and S/N actuator is installed. 

(2) If any affected P/N and S/N actuator is 

identified with the ‘‘P180–32–29’’ marking 

on the name plate, no further action is 

required by this AD on that actuator. 

(3) If one or both affected MLG actuators 

are not identified with the ‘‘P180–32–29’’ 

marking on the name plate, before reaching 

a total of 3,000 hours TIS on the actuator or 

within the next 150 hours TIS after the 

effective date of this AD, whichever occurs 

later, replace the affected actuator(s) with 

serviceable parts following Part B of the 

Accomplishment Instructions of Piaggio Aero 

Industries S.p.A. Mandatory Service Bulletin 

No. 80–0304, dated July 9, 2010. 

(4) After the effective date of this AD, do 

not install any MLG actuator having an 

affected P/N and S/N, unless it is identified 

with the ‘‘P180–32–29’’ marking on the name 

plate. 

Note 1: There is a warranty expiration date 

for the replacement of the actuators. The 

FAA recommends owners/operators that 

have affected main landing gear actuators 

contact the manufacturer immediately and 

replace the actuators under warranty. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: The 

compliance times of the MCAI are presented 

in flight cycles (landings). When doing the 

conversion for these airplanes from flight 

cycles to hours TIS, the FAA has estimated 

that 1 flight cycle is equal to 1 hour TIS 

based on the utility of this class of airplane. 

Since operators of aircraft of U.S. registry are 

required to keep track of hours TIS, the 

compliance time of this AD is in hours TIS. 

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: Mike Kiesov, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

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

4090; e-mail: mike.kiesov@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 European Aviation 

Safety Agency (EASA) AD No.: 2011–0133, 

dated July 12, 2011; and Piaggio Aero 

Industries S.p.A. Mandatory Service Bulletin 

No. 80–0304, dated July 9, 2010, for related 

information. For service information related 

to this AD, contact Piaggio Aero Industries 

S.p.A Airworthiness Office; Via Luigi 

Cibrario, 4–16154 Genova–Italy; telephone: 

+39 010 6481353; fax: +39 010 6481881; 

E-mail: airworthiness@piaggioaero.it. 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. 

Issued in Kansas City, Missouri, on August 

26, 2011. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–22387 Filed 8–31–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0915; Directorate 

Identifier 2011–NM–020–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD would require repetitive general 

visual inspections for broken or missing 

latch pins of the lower sills of the 

forward and aft lower lobe cargo doors; 

repetitive detailed inspections for 

cracking of the latch pins; and 

corrective actions if necessary. This 

proposed AD was prompted by reports 

of fractured latch pins found in service; 

investigation revealed that the cracking 

and subsequent fracture were initiated 

by fatigue and propagated by a 

combination of fatigue and stress 

corrosion. We are proposing this AD to 

detect and correct fractured or broken 

latch pins, which could result in a 

forward or aft lower lobe cargo door 

opening and detaching during flight, 

and consequent rapid decompression of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by October 17, 2011. 

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. 


emcdonald on DSK2BSOYB1PROD with PROPOSALS