Federal Register / Vol. 74, No. 149 / Wednesday, August 5, 2009 / Proposed Rules 38993 

functional check of the nose landing gear 

(NLG) steering manifold. Follow the 

accomplishment instructions of Piaggio Aero 

Industries S.p.A. Service Bulletin 

(Mandatory) N. 80–0249, rev. 1, dated May 

27, 2009. 

(2) Upon installation of a NLG steering 

manifold on any airplane, do a functional 

check of the NLG steering manifold. 

Repetitively thereafter at intervals not to 

exceed every 165 hours TIS, do a functional 

check of the NLG steering manifold. Follow 

the accomplishment instructions of Piaggio 

Aero Industries S.p.A. Service Bulletin 

(Mandatory) N. 80–0249, rev. 1, dated May 

27, 2009. 

(3) If during any inspection required in 

paragraphs (f)(1) and (f)(2) of this AD a NLG 

steering manifold does not pass the 

functional tests, using the compliance times 

in the accomplishment instructions of 

Piaggio Aero Industries S.p.A. Service 

Bulletin (Mandatory) N. 80–0249, rev. 1, 

dated May 27, 2009, replace the NLG steering 

manifold following (for S/N 1004 through 

1104) pages 1 through 8; 201 through 216; 

and 501 through 506, of Piaggio Aero Piaggio 

P.180 Avanti Maintenance Manual, Report 

No. 9066, 32–50–00, revised June 16, 2008; 

or (for S/N 1105 and greater) pages 1 through 

8; 201 through 216; and 501 through 506, of 

Piaggio Aero Piaggio P.180 Avanti II 

Maintenance Manual, Report No. 180–MAN– 

0200–01105, 32–50–00, revised December 19, 

2008. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Sarjapur Nagarajan, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

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

329–4090. 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, 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 

(h) Refer to MCAI EASA AD 2009–0129, 

dated June 19, 2009; and Piaggio Aero 

Industries S.p.A. Service Bulletin 

(Mandatory) N. 80–0249, rev. 1, dated May 

27, 2009, for related information. 

Issued in Kansas City, Missouri, on July 30, 

2009. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–18685 Filed 8–4–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0703; Directorate 

Identifier 2009–NM–093–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–600–2C10 (Regional Jet 

Series 700, 701 & 702) Airplanes, 

Model CL–600–2D15 (Regional Jet 

Series 705) Airplanes, and Model CL– 

600–2D24 (Regional Jet Series 900) 

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: There have been four 

reports of loose or detached main 

landing gear torque link apex pin 

locking plate and the locking plate 

retainer bolt. This condition could 

result in torque link apex pin 

disengagement, heavy vibration during 

landing, damage to main landing gear 

components and subsequent main 

landing gear collapse. 

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 September 4, 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. 

• 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 Bombardier, 

Inc., 400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 

514–855–5000; fax 514–855–7401; 

e-mail thd.crj@aero.bombardier.com; 

Internet http://www.bombardier.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: 

Pong Lee, Aerospace Engineer, Airframe 

and Mechanical Systems Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7324; fax 

(516) 794–5531. 

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–2009–0703; Directorate Identifier 

2009–NM–093–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:// 


srobinson on DSKHWCL6B1PROD with PROPOSALS
38994 Federal Register / Vol. 74, No. 149 / Wednesday, August 5, 2009 / Proposed Rules 

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 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2009–20, 

dated May 1, 2009 (referred to after this 

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

condition for the specified products. 

The MCAI states: 

There have been four reports of loose or 

detached main landing gear torque link apex 

pin locking plate and the locking plate 

retainer bolt. This condition could result in 

torque link apex pin disengagement, heavy 

vibration during landing, damage to main 

landing gear components and subsequent 

main landing gear collapse. 

Investigation has determined that incorrect 

stack-up tolerances of the apex joint or 

improper installation of the locking plate and 

apex nut could result in torque link apex pin 

disengagement. This directive mandates [a 

one-time detailed] inspection of the torque 

link apex joint [for correct installation and 

damage, and corrective actions if necessary] 

and replacement of the torque link apex nut. 

The corrective actions include reinstalling parts that are not correctly 

installed and replacing damaged parts. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier has issued Service 

Bulletin 670BA–32–019, Revision A, 

dated September 18, 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 361 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 $80 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$115,520, or $320 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: 

Bombardier, Inc. (Formerly Canadair): 

Docket No. FAA–2009–0703; Directorate 

Identifier 2009–NM–093–AD. 

Comments Due Date 

(a) We must receive comments by 

September 4, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the Bombardier 

airplanes identified in paragraphs (c)(1) and 

(c)(2) of this AD, certificated in any category. 

(1) Model CL–600–2C10 (Regional Jet 

Series 700, 701 & 702) airplanes, serial 

numbers (S/Ns) 10003 and subsequent. 

(2) Model CL–600–2D15 (Regional Jet 

Series 705) airplanes and Model CL–600– 

2D24 (Regional Jet Series 900) airplanes, 

S/Ns 15001 and subsequent. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

There have been four reports of loose or 

detached main landing gear torque link apex 

pin locking plate and the locking plate 

retainer bolt. This condition could result in 

torque link apex pin disengagement, heavy 

vibration during landing, damage to main 

landing gear components and subsequent 

main landing gear collapse. 

Investigation has determined that incorrect 

stack-up tolerances of the apex joint or 

improper installation of the locking plate and 

apex nut could result in torque link apex pin 

disengagement. This directive mandates [a 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 74, No. 149 / Wednesday, August 5, 2009 / Proposed Rules 38995 

one-time detailed] inspection of the torque 

link apex joint [for correct installation and 

damage, and corrective actions if necessary] 

and replacement of the torque link apex nut. 

The corrective actions include re-installing 

parts that are not correctly installed and 

replacing damaged parts. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) For Model CL–600–2C10 airplanes, S/ 

Ns 10003 through 10223 inclusive; and 

Model CL–600–2D15 and Model CL–600– 

2D24 airplanes, S/Ns 15001 through 15035 

inclusive, 15038, 15039, and 15042: Within 

900 flight hours after the effective date of this 

AD, perform a one-time detailed inspection 

and all applicable corrective actions on the 

torque link apex joint, in accordance with 

Part A of the Accomplishment Instructions of 

Bombardier Service Bulletin 670BA–32–019, 

Revision A, dated September 18, 2008, 

except as provided by paragraph (f)(5) of this 

AD. Do all applicable corrective actions 

before further flight. 

(2) For Model CL–600–2C10 airplanes, S/ 

Ns 10003 through 10239 inclusive; and 

Model CL–600–2D15 and CL–600–2D24 

airplanes, S/Ns 15001 through 15057 

inclusive: Within 4,500 flight hours after the 

effective date of this AD, replace or rework 

the apex nut, in accordance with Part B of 

the Accomplishment Instructions of 

Bombardier Service Bulletin 670BA–32–019, 

Revision A, dated September 18, 2008. 

(3) As of the effective date of this AD, no 

person may install, on any airplane, a 

replacement MLG shock strut assembly 

identified in paragraph (f)(3)(i) or (f)(3)(ii) of 

this AD, unless it has been reworked in 

accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–019, Revision A, 

dated September 18, 2008. 

(i) Part number (P/N) 49000–11 through 

49000–22 inclusive, and with a serial number 

in the range of S/N 0001 through 0284 

inclusive (the serial number can start with 

‘‘MA,’’ ‘‘MAL,’’ or ‘‘MA-’’). 

(ii) P/N 49050–5 through 49050–10 

inclusive, and with a serial number in the 

range of S/N 1001 through 1114 inclusive 

(the serial number can start with ‘‘MA,’’ 

‘‘MAL,’’ or ‘‘MA-’’). 

(4) Inspections, corrective actions, 

replacements, and rework accomplished 

before the effective date of this AD in 

accordance with Bombardier Service Bulletin 

670BA–32–019, dated March 16, 2006, are 

considered acceptable for compliance with 

the corresponding actions specified in this 

AD. 

(5) The inspections specified in paragraph 

(f)(1) of this AD are not required if the actions 

specified in paragraph (f)(2) of this AD have 

already been accomplished; or if Bombardier 

Repair Engineering Order 670–32–11–0022, 

dated October 22, 2005; or Goodrich Service 

Concession Request SCR 0056–05, dated 

October 22, 2005; has been incorporated. 

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, 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: Pong 

Lee, Aerospace Engineer, Airframe and 

Mechanical Systems Branch, ANE–171, FAA, 

New York Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, New 

York 11590; telephone (516) 228–7324; 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. 

(h) Special Flight Permits: Special flight 

permits, as described in Section 21.197 and 

Section 21.199 of the Federal Aviation 

Regulations (14 CFR 21.197 and 21.199), are 

not allowed. 

Related Information 

(i) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–20, dated May 1, 2009; 

and Bombardier Service Bulletin 670BA–32– 

019, Revision A, dated September 18, 2008; 

for related information. 

Issued in Renton, Washington, on July 28, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–18731 Filed 8–4–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0682; Directorate 

Identifier 2008–NM–200–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–300, 747–400, 

747SR, and 747SP Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Boeing Model 747 airplanes. The 

existing AD currently requires repetitive 

inspections for cracking, and repair as 

necessary, of lower lobe body frames 

(sections 42 and 46) of the fuselage. The 

existing AD also provides for optional 

modification of the frames, which 

terminates the repetitive inspections. 

This proposed AD would require 

additional repetitive inspections for 

cracking of certain fuselage frames, and 

corrective actions if necessary. This 

proposed AD would also revise the AD 

applicability. This proposed AD results 

from a new report of a crack found in 

a body frame with a tapered side guide 

bracket at fuselage station 1800, located 

on the left side between stringers 39 and 

40; the frame was severed. We are 

proposing this AD to detect and correct 

the loss of structural integrity of the 

fuselage, which could result in rapid 

depressurization of the airplane. 

DATES: We must receive comments on 

this proposed AD by September 21, 

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. 

• 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. 


srobinson on DSKHWCL6B1PROD with PROPOSALS