Federal Register / Vol. 75, No. 96 / Wednesday, May 19, 2010 / Proposed Rules 27961 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$765. 

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: 

BAE Systems (Operations) Limited: Docket 

No. FAA–2010–0477; Directorate 

Identifier 2009–NM–226–AD. 

Comments Due Date 

(a) We must receive comments by July 6, 

2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to BAE SYSTEMS 

(Operations) Limited Model BAe 146–100A, 

–200A, and –300A series airplanes and 

Model Avro 146–RJ70A, 146–RJ85A, and 

146–RJ100A airplanes, certificated in any 

category, all serial numbers, except those 

airplanes modified to freighter configuration 

in accordance with BAE Systems 

modification No. HCM50200B. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight Controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Three events have been reported where 

insulation material was found to be fouling 

pulleys in the aileron interconnect circuit in 

the cabin roof area. 

Interference between the cable and the 

insulation bag causes the material to be 

drawn into the gap between the pulley and 

the pulley guard. This condition, if not 

detected and corrected, could lead to 

restricted aileron movement and 

consequently, reduced control of the 

aeroplane. 

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. 

Actions 

(g) Within 6 months after the effective date 

of this AD, install new aileron interconnect 

cable pulley guards, in accordance with 

paragraph 2.C. ‘‘Modification’’ of the 

Accomplishment Instructions of BAE 

SYSTEMS (Operations) Limited Modification 

Service Bulletin SB.27–183–36246A, dated 

December 9, 2008. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(h) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: Todd Thompson, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1175; fax (425) 227–1149. 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. 

(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 FAAapproved 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, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(i) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2009–0205, 

Revision 1, dated January 12, 2010; and BAE 

SYSTEMS (Operations) Limited Modification 

Service Bulletin SB.27–183–36246A, dated 

December 9, 2008; for related information. 

Issued in Renton, Washington, on May 4, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–11903 Filed 5–18–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0479 Directorate 

Identifier 2009–NM–220–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Model F.28 Mark 0070 

and 0100 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 


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27962 Federal Register / Vol. 75, No. 96 / Wednesday, May 19, 2010 / Proposed Rules 

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: Recently, a brake fire was 

reported which was caused by a 

ruptured brake piston. The fire was 

quickly extinguished but caused damage 

to the paint and hydraulic/electrical 

harness and its components. Detailed 

investigation showed that a hydraulic 

lock must have been present close to the 

affected brake creating enough internal 

pressure to rupture the piston. The most 

probable scenario for the hydraulic lock 

is a loosened (not necessarily 

disconnected) brake QD [quickdisconnect] coupling. Further 

investigation of the service experience 

files at Fokker Services showed that 

more brake fires have occurred on 

aeroplanes in a pre-mod SBF100–32– 

127 configuration. The unsafe condition 

is loss of braking capability and possible 

brake fires, which could reduce the 

ability of the flightcrew to safely land 

the airplane. 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 July 6, 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. 

For service information identified in 

this proposed 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. 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. 

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 proposed 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: 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: 

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–2010–0479; Directorate Identifier 

2009–NM–220–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 based on those comments. 

We have lengthened the 30-day 

comment period for proposed ADs that 

address MCAI originated by aviation 

authorities of other countries to provide 

adequate time for interested parties to 

submit comments. The comment period 

for these proposed ADs is now typically 

45 days, which is consistent with the 

comment period for domestic transport 

ADs. 

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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2009–0176, 

dated August 6, 2009 (referred to after 

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

condition for the specified products. 

The MCAI states: 

During 1995, several reports were received 

of brake QD [quick-disconnect] couplings 

loosened and/or disconnected during 

operation. In a few cases, residual brake 

pressure was trapped in the affected brake, 

causing asymmetric braking and/or resulting 

in hot brakes. Loosened couplings may cause 

a hydraulic leak with the risk of a brake fire. 

Investigation revealed that the installation of 

the brake QD couplings must be done with 

care and that the locking teeth on the light 

alloy sleeve are prone to wear. The Fokker 

70/100 Aircraft Maintenance Manual (AMM) 

has been revised to include additional 

information to ensure correct removal and 

installation of the couplings. 

In 1997, Fokker Services issued SBF100– 

32–106, recommending the introduction of 

QD couplings with corrosion resistant steel 

(CRES) sleeves that would prevent excessive 

wear of the locking teeth on the light alloy 

sleeve. In response to more reported cases of 

loosened QD couplings resulting in brake 

problems, further improved QD couplings 

were introduced in 2001 through SBF100– 

32–127. These couplings increase the 

reliability of the brake system. 

Recently, a brake fire was reported which 

was caused by a ruptured brake piston. The 

fire was quickly extinguished but caused 

damage to the paint and hydraulic/electrical 

harness and its components. Detailed 

investigation showed that a hydraulic lock 

must have been present close to the affected 

brake creating enough internal pressure to 

rupture the piston. The most probable 

scenario for the hydraulic lock is a loosened 

(not necessarily disconnected) brake QD 

coupling. Further investigation of the service 

experience files at Fokker Services showed 

that more brake fires have occurred on 

aeroplanes in a pre-mod SBF100–32–127 

configuration. 

In order to reduce the probability of a fluid 

fire as described in CS (certification 

specification) 25.863, additional action is 

deemed necessary. 

For the reasons described above, this AD 

requires repetitive [detailed] inspections [for 

wear] of the affected brake QD couplings and 

replacement of the QD couplings with 

improved units. Installation of the improved 

QD couplings terminates the repetitive 

inspections requirements. 

The unsafe condition is loss of braking 

capability and possible brake fires, 

which could reduce the ability of the 

flightcrew to safely land the airplane. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Fokker Services B.V. has issued 

Service Bulletin SBF100–32–156, 

Revision 1, dated June 29, 2009. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 


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Federal Register / Vol. 75, No. 96 / Wednesday, May 19, 2010 / Proposed Rules 27963 

FAA’s Determination and Requirements 

of This 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 the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

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 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 

Based on the service information, we 

estimate that this proposed AD would 

affect about 16 products of U.S. registry. 

We also estimate that it would take 

about 4 work-hours 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 $4,814 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these costs. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$82,464, or $5,154 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 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: 

Fokker Services B.V.: Docket No. FAA– 

2010–0479; Directorate Identifier 2009– 

NM–220–AD. 

Comments Due Date 

(a) We must receive comments by July 6, 

2010. 

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, all serial 

numbers, with any brake quick-disconnect 

(QD) coupling having part number (P/N) 

AE70690E, AE70691E, AE99111E, or 

AE99119E installed. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing Gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During 1995, several reports were received 

of brake QD couplings loosened and/or 

disconnected during operation. In a few 

cases, residual brake pressure was trapped in 

the affected brake, causing asymmetric 

braking and/or resulting in hot brakes. 

Loosened couplings may cause a hydraulic 

leak with the risk of a brake fire. 

Investigation revealed that the installation of 

the brake QD couplings must be done with 

care and that the locking teeth on the light 

alloy sleeve are prone to wear. The Fokker 

70/100 Aircraft Maintenance Manual (AMM) 

has been revised to include additional 

information to ensure correct removal and 

installation of the couplings. 

In 1997, Fokker Services issued SBF100– 

32–106, recommending the introduction of 

QD couplings with corrosion resistant steel 

(CRES) sleeves that would prevent excessive 

wear of the locking teeth on the light alloy 

sleeve. In response to more reported cases of 

loosened QD couplings resulting in brake 

problems, further improved QD couplings 

were introduced in 2001 through SBF100– 

32–127. These couplings increase the 

reliability of the brake system. 

Recently, a brake fire was reported which 

was caused by a ruptured brake piston. The 

fire was quickly extinguished but caused 

damage to the paint and hydraulic/electrical 

harness and its components. Detailed 

investigation showed that a hydraulic lock 

must have been present close to the affected 

brake creating enough internal pressure to 

rupture the piston. The most probable 

scenario for the hydraulic lock is a loosened 

(not necessarily disconnected) brake QD 

coupling. Further investigation of the service 

experience files at Fokker Services showed 

that more brake fires have occurred on 

aeroplanes in a pre-mod SBF100–32–127 

configuration. 

In order to reduce the probability of a fluid 

fire as described in CS (certification 

specification) 25.863, additional action is 

deemed necessary. 

For the reasons described above, this AD 

requires repetitive [detailed] inspections [for 

wear] of the affected brake QD couplings and 

replacement of the QD couplings with 

improved units. Installation of the improved 

QD couplings terminates the repetitive 

inspections requirements. 


erowe on DSK5CLS3C1PROD with PROPOSALS-1
27964 Federal Register / Vol. 75, No. 96 / Wednesday, May 19, 2010 / Proposed Rules 

The unsafe condition is loss of braking 

capability and possible brake fires, which 

could reduce the ability of the flightcrew to 

safely land the airplane. 

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. 

Actions 

(g) Do the following actions. 

(1) Within 6 months after the effective date 

of this AD, do a detailed inspection for wear 

of the brake QD couplings by measuring 

dimension ‘‘A,’’ in accordance with Part 1 of 

the Accomplishment Instructions of Fokker 

Service Bulletin SBF100–32–156, Revision 1, 

dated June 29, 2009. Repeat the inspection 

thereafter at the applicable intervals specified 

in Table 1 of this AD, except as required by 

paragraph (g)(2) of this AD. 

TABLE 1—REPETITIVE INSPECTION INTERVALS

If dimension ‘‘A’’ is— 

Repeat the inspection 

at intervals not to 

exceed— 

Greater than or equal to 0.76 mm ......................................................................................................................................... 6 months. 

Less than 0.76 mm but greater than or equal to 0.72 mm ................................................................................................... 3 months. 

Less than 0.72 mm but greater than or equal to 0.68 mm ................................................................................................... 30 days. 

Less than 0.68 mm but greater than or equal to 0.61 mm ................................................................................................... 7 days. 

Less than 0.61 mm but greater than 0.53 mm ...................................................................................................................... 24 hours. 

(2) If, during any inspection required by 

paragraph (g)(1) of this AD, dimension ‘‘A’’ on 

any brake QD coupling is less than or equal 

to 0.53 mm, before further flight, replace the 

affected brake QD coupling with an improved 

unit having P/N AE73059E or P/N AE73091E, 

as applicable, in accordance with Part 2 of 

the Accomplishment Instructions of Fokker 

Service Bulletin SBF100–32–156, Revision 1, 

dated June 29, 2009. 

(3) Within 24 months after the effective 

date of this AD, replace all remaining brake 

QD couplings having P/N AE70690E, P/N 

AE70691E, P/N AE99111E, and P/N 

AE99119E with improved units, in 

accordance with Part 2 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–32–156, Revision 1, 

dated June 29, 2009. 

(4) Installation of brake QD couplings with 

an improved unit having P/N AE73059E or 

P/N AE73091E at all locations terminates the 

repetitive inspections required by paragraph 

(g)(1) of this AD. 

(5) Replacing the brake QD couplings is 

also acceptable for compliance with the 

corresponding requirements of paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD if done 

before the effective date of this AD, in 

accordance with any of the service bulletins 

specified in Table 2 of this AD: 

TABLE 2—FOKKER CREDIT SERVICE BULLETINS

Fokker Service Bulletins Revision Date 

Fokker Service Bulletin SBF100–32–127 ............................................................... Original ................................................... July 20, 2001. 

Fokker Service Bulletin SBF100–32–127 ............................................................... 1 ............................................................. March 6, 2009. 

Fokker Service Bulletin SBF100–32–156 ............................................................... Original ................................................... March 6, 2009. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(h) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 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. 

(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, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(i) Refer to MCAI EASA Airworthiness 

Directive 2009–0176, dated August 6, 2009; 

and Fokker Service Bulletin SBF100–32–156, 

Revision 1, dated June 29, 2009; for related 

information. 

Issued in Renton, Washington, on May 4, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–11904 Filed 5–18–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1157; Directorate 

Identifier 2009–NE–26–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc (RR) RB211–22B and RB211–524 

Series Turbofan Engines 

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 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: Several low pressure 

turbine (LPT) shafts have been found 


erowe on DSK5CLS3C1PROD with PROPOSALS-1