8618 Federal Register / Vol. 76, No. 31 / Tuesday, February 15, 2011 / Rules and Regulations 

Independence Ave., SW., Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(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. Send information to ATTN: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6577; fax (425) 

917–6590. Information may be e-mailed to: 9- 

ANM-Seattle-ACO-AMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(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. 

Material Incorporated by Reference 

(m) You must use Boeing Special Attention 

Service Bulletin 767–57–0118, Revision 1, 

dated October 21, 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 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. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on January 

28, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–2515 Filed 2–14–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1038; Directorate 

Identifier 2009–NM–250–AD; Amendment 

39–16601; AD 2011–04–01] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Model F.28 Mark 0070 

and 0100 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) 

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: 

During a normal walkaround check on a 

F28 Mark 0100 aeroplane, a large crack was 

discovered in the lower portion of the right 

(RH) MLG [main landing gear] piston. The 

affected MLG unit had accumulated 7909 

flight cycles (FC) at the time of detection. 

* * * 

This condition, if not detected and 

corrected, could lead to MLG failure, 

possibly resulting in loss of control of the 

aeroplane during the landing roll-out. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

March 22, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 22, 2011. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

425–227–1137; fax 425–227–1149. 

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 October 21, 2010 (75 FR 

64963). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During a normal walkaround check on a 

F28 Mark 0100 aeroplane, a large crack was 

discovered in the lower portion of the right 

(RH) MLG [main landing gear] piston. The 

affected MLG unit had accumulated 7909 

flight cycles (FC) at the time of detection. The 

piston has been sent to Goodrich, the landing 

gear manufacturer, for detailed investigation. 

This condition, if not detected and 

corrected, could lead to MLG failure, 

possibly resulting in loss of control of the 

aeroplane during the landing roll-out. 

For the reasons described above, this AD 

requires a one-time detailed visual inspection 

of the MLG pistons, the replacement of any 

MLG pistons on which cracks are detected, 

and the reporting of all findings to the 

aeroplane TC [type certificate] holder. The 

inspection results, in combination with the 

findings of the crack/metallurgical 

investigation of the cracked piston by 

Goodrich, will be used to determine the 

necessity of additional and/or more detailed 

inspections, or any other corrective action. 

This AD is considered an interim measure, 

and further action is likely to follow. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Request To Update Reference to MCAI 

The European Aviation Safety Agency 

(EASA) requested that we update the 

NPRM to refer to EASA AD 2009– 

0221R1, dated June 30, 2010. This 

EASA AD corrects a typographical error, 

which was the source of a difference 

between the FAA NPRM and the EASA 

AD. 

We agree with the EASA’s request to 

update this final rule to refer to the 

latest EASA AD. We have also revised 

Note 1 of the final rule to state that there 

are no differences between the EASA 

AD and the FAA AD. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 


jdjones on DSK8KYBLC1PROD with RULES
Federal Register / Vol. 76, No. 31 / Tuesday, February 15, 2011 / Rules and Regulations 8619 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

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 our FAA 

policies. Any such differences are 

highlighted in a Note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 6 

products of U.S. registry. We also 

estimate that it will take about 3 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $1,530 or $255 per product. 

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 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 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 Operations office 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 Operations 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: 

2011–04–01 Fokker Services, B.V.: 

Amendment 39–16601. Docket No. 

FAA–2010–1038; Directorate Identifier 

20009–NM–250–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 22, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Fokker Services B.V. 

Model F.28 Mark 0070 and 0100 airplanes, 

certificated in any category, equipped with 

Goodrich (formerly Menasco, Colt Industries) 

main landing gear (MLG) units having part 

number (P/N) 41050–7, 41050–8, 41050–9, 

41050–10, 41050–11, 41050–12, 41050–13, 

41050–14, 41050–15, 41050–16, 41060–1, 

41060–2, 41060–3, 41060–4, 41060–5, or 

41060–6. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During a normal walkaround check on a 

F28 Mark 0100 aeroplane, a large crack was 

discovered in the lower portion of the right 

(RH) MLG piston. The affected MLG unit had 

accumulated 7909 flight cycles (FC) at the 

time of detection. The piston has been sent 

to Goodrich, the landing gear manufacturer, 

for detailed investigation. 

This condition, if not detected and 

corrected, could lead to MLG failure, 

possibly resulting in loss of control of the 

aeroplane during the landing roll-out. 

For the reasons described above, this AD 

requires a one-time detailed visual inspection 

of the MLG pistons, the replacement of any 

MLG pistons on which cracks are detected, 

and the reporting of all findings to the 

aeroplane TC [type certificate] holder. The 

inspection results, in combination with the 

findings of the crack/metallurgical 

investigation of the cracked piston by 

Goodrich, will be used to determine the 

necessity of additional and/or more detailed 

inspections, or any other corrective action. 

This AD is considered an interim measure, 

and further action is likely to follow. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Inspection 

(g) Within 30 days after the effective day 

of this AD, do a detailed visual inspection for 

cracks of the MLG pistons, in accordance 

with the Accomplishment Instructions of 

Fokker Service Bulletin SBF100–32–158, 

dated October 2, 2009. 

(h) If any cracked MLG piston is found 

during the inspection required by paragraph 

(g) of this AD, before further flight replace the 

affected piston with a serviceable part, in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–32–158, dated October 2, 2009. 

(i) At the applicable time specified in 

paragraph (i)(1) or (i)(2) of this AD, report the 

inspection results (including no findings) to 

Fokker Services B.V. by using the 

Questionnaire provided in Fokker Service 

Bulletin SBF100–32–158, dated October 2, 

2009. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 


jdjones on DSK8KYBLC1PROD with RULES
8620 Federal Register / Vol. 76, No. 31 / Tuesday, February 15, 2011 / Rules and Regulations 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: Tom Rodriguez, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 425– 

227–1137; fax 425–227–1149. 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) 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: 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 

(k) For related information, refer to MCAI 

European Aviation Safety Agency 

Airworthiness Directive 2009–0221R1, dated 

June 30, 2010; and Fokker Service Bulletin 

SBF100–32–158, dated October 2, 2009. 

Material Incorporated by Reference 

(l) You must use Fokker Service Bulletin 

SBF100–32–158, dated October 2, 2009, 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 Fokker Services B.V., 

Technical Services Dept., P.O. Box 231, 2150 

AE Nieuw-Vennep, the Netherlands; 

telephone +31 (0)252–627–350; fax +31 

(0)252–627–211; e-mail 

technicalservices.fokkerservices@stork.com; 

Internet http://www.myfokkerfleet.com. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on January 

31, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–2823 Filed 2–14–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0594; Directorate 

Identifier 98–ANE–43–AD; Amendment 39– 

16604; AD 2011–04–04] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney JT8D–209, –217, –217A, 

–217C, and –219 Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

Pratt & Whitney (PW) JT8D–209, –217, 

–217A, –217C, and –219 turbofan 

engines. That AD currently requires 

revisions to the engine manufacturer’s 

time limits section (TLS) to include 

enhanced inspection of selected critical 

life-limited parts at each piece-part 

opportunity. This new AD modifies the 

TLS of the manufacturer’s engine 

manual and an air carrier’s approved 

continuous airworthiness maintenance 

program to incorporate additional 

inspection requirements. This AD was 

prompted by PW developing, and the 

FAA approving, improved inspection 

procedures for the critical life-limited 

parts. The mandatory inspections are 

needed to identify those critical rotating 

parts with conditions, which if allowed 

to continue in service, could result in 

uncontained failures. We are issuing 

this AD to prevent critical life-limited 

rotating engine part failure, which could 

result in an uncontained engine failure 

and damage to the airplane. 

DATES: This AD is effective March 22, 

2011. 

ADDRESSES: 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

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 FURTHER INFORMATION CONTACT: Ian 

Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7178, fax: 781–238– 

7199; e-mail: ian.dargin@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2005–18–02, 

Amendment 39–14242 (70 FR 71610, 

November 29, 2005). That AD applies to 

the specified products. The NPRM 

published in the Federal Register on 

August 18, 2010 (75 FR 50945). That 

NPRM proposed to modify the TLS of 

the manufacturer’s engine manual and 

an air carrier’s approved continuous 

airworthiness maintenance program to 

incorporate additional inspection 

requirements. PW has developed and 

the FAA has approved improved 

inspection procedures for the critical 

life-limited parts. The mandatory 

inspections are needed to identify those 

critical rotating parts with conditions 

which, if allowed to continue in service, 

could result in uncontained failures. 

Comment 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the proposal and the FAA’s 

response to the comment. 

Request 

One commenter, American Airlines, 

requested that we change the 


jdjones on DSK8KYBLC1PROD with RULES