Federal Register / Vol. 74, No. 186 / Monday, September 28, 2009 / Proposed Rules 49349 

To correct the unsafe condition, this 

[Canadian airworthiness] directive mandates 

the installation of thermal fuses in the No. 1 

and No. 2 hydraulic systems and the 

introduction of Fuel System Limitations 

(FSL) and Critical Design Configuration 

Control Limitations (CDCCL) associated with 

this design change. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 6,000 flight hours after the 

effective date of this AD, modify the aircraft 

hydraulic system by installing thermal fuses 

according to the Accomplishment 

Instructions of Bombardier Service Bulletin 

670BA–29–005, Revision A, dated January 

29, 2009. 

(2) Before or concurrently with the actions 

required by paragraph (f)(1) of this AD, revise 

the Airworthiness Limitations Section (ALS) 

of the Instructions for Continued 

Airworthiness to incorporate the tasks 

identified in Table 1 of this AD as specified 

in Bombardier Temporary Revision (TR) 2– 

269, dated December 18, 2008, to Section 3, 

‘‘Fuel Systems Limitations,’’ of Part 2 of the 

Bombardier CL–600–2C10, CL–600–2D15, 

and CL–600–2D24 Maintenance 

Requirements Manual. The initial 

compliance time for the task is within 10,000 

flight hours after doing the action required by 

paragraph (f)(1) of this AD, or within 60 days 

after the effective date of this AD, whichever 

occurs later, and the limitation task must be 

accomplished thereafter at the ‘‘limiting 

interval’’ specified in Bombardier TR 2–269, 

dated December 18, 2008, except as provided 

by paragraphs (f)(4) and (g)(1) of this AD. 

TABLE 1—FUEL SYSTEM LIMITATION

TASK

Task No. Task description 

29–30–00–603 Hydraulic System No. 1 and 

No. 2 Thermal Fuse: Discard the system No. 1 and 

No. 2 thermal fuse (Post 

Modsum 670T112042 or 

SB 670BA–29–005). 

(3) Before or concurrently with the actions 

required by paragraph (f)(1) of this AD, revise 

the ALS of the Instructions for Continued 

Airworthiness to incorporate the CDCCL data 

specified in Bombardier TR 2–268, dated 

December 18, 2008, to Section 3, ‘‘Fuel 

System Limitations,’’ of Part 2 of the 

Bombardier CL–600–2C10, CL–600–2D15 

and CL–600–2D24 Maintenance 

Requirements Manual. 

Note 2: The actions required by paragraphs 

(f)(2) and (f)(3) of this AD may be done by 

inserting a copy of the TR into the 

maintenance requirements manual. When the 

TR has been included in the general revision 

of the maintenance program, the general 

revision may be inserted into the 

maintenance requirements manual, provided 

the relevant information in the general 

revision is identical to that in the TR, and the 

temporary revision may be removed. 

(4) After accomplishing the actions 

specified in paragraphs (f)(2) and (f)(3) of this 

AD, no alternative limitation tasks, limitation 

task intervals, or CDCCLs may be used unless 

the limitation task, limitation task interval, or 

CDCCL is approved as an alternative method 

of compliance (AMOC) in accordance with 

the procedures specified in paragraph (g)(1) 

of this AD. 

(5) Actions accomplished before the 

effective date of this AD in accordance with 

Bombardier Service Bulletin 670BA–29–005, 

dated December 18, 2008, are considered 

acceptable for compliance with the 

corresponding action specified in paragraph 

(f)(1) of this AD. 

Note 3: Notwithstanding any other 

maintenance or operational requirements, 

components that have been identified as 

airworthy or installed on the affected 

airplanes before the revision of the 

airworthiness limitations section, as required 

by paragraphs (f)(1) and (f)(2) of this AD, do 

not need to be reworked in accordance with 

the CDCCLs. However, once the 

airworthiness limitations section has been 

revised, future maintenance actions on these 

components must be done in accordance 

with the CDCCLs. 

FAA AD Differences 

Note 4: 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, New York Aircraft 

Certification Office (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: 

Christopher Alfano, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE–171, 

FAA, New York Aircraft Certification Office, 

1600 Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228–7340; 

fax (516) 794–5531. 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, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–09, dated March 9, 2009; 

Bombardier Service Bulletin 670BA–29–005, 

Revision A, dated January 29, 2009; 

Bombardier TR 2–268, dated December 18, 

2008, to Section 3, ‘‘Fuel System 

Limitations,’’ of Part 2 of the Bombardier CL– 

600–2C10, CL–600–2D15, and CL–600–2D24 

Maintenance Requirements Manual; and 

Bombardier TR 2–269, dated December 18, 

2008, to Section 3, ‘‘Fuel System 

Limitations,’’ of Part 2 of the Bombardier CL– 

600–2C10, CL–600–2D15, and CL–600–2D24 

Maintenance Requirements Manual; for 

related information. 

Issued in Renton, Washington, on 

September 18, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–23296 Filed 9–25–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0793; Directorate 

Identifier 2009–NM–051–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Model F.28 Mark 0070 and 0100 

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 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 cases have been reported where a 

passenger door actuator detached from the 

passenger door. This caused the passenger 

door to drop to the platform in an 

uncontrolled manner. 

This condition, if not corrected, could 

result in injury to persons on the ground and 

damage to the aircraft. 

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 28, 2009. 

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. 


CPrice-Sewell on DSKGBLS3C1PROD with PROPOSALS
49350 Federal Register / Vol. 74, No. 186 / Monday, September 28, 2009 / Proposed Rules 

• 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; email 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 

or 425–227–1152. 

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–2009–0793; Directorate Identifier 

2009–NM–051–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 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 2009–0026, 

dated February 17, 2009 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

Several cases have been reported where a 

passenger door actuator detached from the 

passenger door. This caused the passenger 

door to drop to the platform in an 

uncontrolled manner. 

This condition, if not corrected, could 

result in injury to persons on the ground and 

damage to the aircraft. 

To address this problem, Fokker Services 

has developed an improved actuator to 

ensure the proper functioning of the door 

opening mechanism. 

For the reason described above, this AD 

requires the replacement of existing airstair 

door actuators with improved actuators. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Fokker Services B.V. has issued 

Service Bulletin SBF100–52–087 and 

Component Service Bulletin R5320–52– 

011, both dated November 10, 2008. 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 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 2 products of U.S. registry. 

We also estimate that it would take 

about 12 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $80 per work-hour. Required 

parts would cost about $4,933 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 

$11,786, or $5,893 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 


CPrice-Sewell on DSKGBLS3C1PROD with PROPOSALS
Federal Register / Vol. 74, No. 186 / Monday, September 28, 2009 / Proposed Rules 49351 

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– 

2009–0793; Directorate Identifier 2009– 

NM–051–AD. 

Comments Due Date 

(a) We must receive comments by October 

28, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Fokker Model F.28 

Mark 0070 and 0100 airplanes, certificated in 

any category, all serial numbers, if equipped 

with an ‘‘airstair’’ type door with a passenger 

door actuator having part number (P/N) 

A26900–401, A82936–701, A82936–705, 

R5320, R5320–1, R5320–12, W26900–401, 

W53200–401, W53200–403, or W53200–405. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 52: Doors. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Several cases have been reported where a 

passenger door actuator detached from the 

passenger door. This caused the passenger 

door to drop to the platform in an 

uncontrolled manner. 

This condition, if not corrected, could 

result in injury to persons on the ground and 

damage to the aircraft. 

To address this problem, Fokker Services 

has developed an improved actuator to 

ensure the proper functioning of the door 

opening mechanism. 

For the reason described above, this AD 

requires the replacement of existing airstair 

door actuators with improved actuators. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 7,500 flight cycles after the 

effective date of this AD, replace the affected 

door actuator with a new or modified unit 

that has a part number not identified in 

paragraph (c) of this AD, in accordance with 

Fokker Service Bulletin SBF100–52–087, 

dated November 10, 2008. 

(2) As of 18 months after the effective date 

of this AD, no person may install on any 

airplane a door actuator with a part number 

listed in paragraph (c) of this AD; 

modification of the actuators in accordance 

with Fokker Component Service Bulletin 

R5320–52–011, dated November 10, 2008, 

changes the part number of the actuator. 

FAA AD Differences 

Note 1: 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, 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 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, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2009– 

0026, dated February 17, 2009; Fokker 

Service Bulletin SBF100–52–087, dated 

November 10, 2008; and Fokker Component 

Service Bulletin R5320–52–011, dated 

November 10, 2008; for related information. 

Issued in Renton, Washington, on 

September 18, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–23299 Filed 9–25–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0794; Directorate 

Identifier 2009–NM–035–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747–400, 747–400D, 747– 

400F, 747SR, and 747SP Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Boeing Model 747 airplanes. This 

proposed AD would require a general 

visual inspection to identify any 

existing repairs of the upper main sill 

outer chord of the left and right side 

main entry door number 1, as 

applicable; repetitive detailed 

inspections for cracks in the upper main 

sill of the door(s); and related 

investigative and corrective actions, if 

necessary. This proposed AD would 

also require repetitive inspections for 

airplanes on which a certain repair is 

done, and corrective actions if 

necessary. This proposed AD results 

from reports of cracks in the main entry 

door number 1 upper main sill outer 

chord, along the bend radius of the 

chord on several airplanes. We are 

proposing this AD to detect and correct 

such cracks, which could result in loss 

of structural integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 12, 

2009. 

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. 


CPrice-Sewell on DSKGBLS3C1PROD with PROPOSALS