Federal Register / Vol. 75, No. 162 / Monday, August 23, 2010 / Proposed Rules 51701 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: The 

MCAI does not include a reporting 

requirement; however, the service bulletin 

recommends reporting. Paragraph (j) of this 

AD specifies a reporting requirement. 

Other FAA AD Provisions 

(l) 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: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; 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 

(m) Refer to MCAI EASA Airworthiness 

Directive 2010–0092, dated May 21, 2010; 

Airbus Mandatory Service Bulletin A300– 

27A6067, Revision 01, dated May 12, 2010; 

and Airbus Mandatory Service Bulletin 

A310–27A2104, Revision 01, dated May 12, 

2010; for related information. 

Issued in Renton, Washington, on August 

16, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–20854 Filed 8–20–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0802; Directorate 

Identifier 2009–NM–256–AD] 

RIN 2120–AA64 

Airworthiness Directives; Learjet Inc. 

Model 45 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 

Learjet Inc. Model 45 airplanes. The 

existing AD currently requires, for 

certain airplanes, repetitive inspections 

for chafing and other damage of the case 

drain tube from the hydraulic pump 

case installed on the left-hand engine, 

and corrective action if necessary. The 

existing AD also requires, for all 

airplanes, repetitive inspections for 

discrepancies of the left engine’s nacelle 

tubing, repetitive inspections for 

evidence of fluid leakage within the left 

engine accessory compartment, and 

corrective actions if necessary. This 

proposed AD would require replacing 

the left engine fuel and hydraulic tubing 

and installing a tubing support channel, 

which would terminate the repetitive 

inspections required in the existing AD. 

This proposed AD also removes 

airplanes from the applicability. This 

proposed AD results from reports of 

chafed hydraulic tubes in the left-hand 

engine. We are proposing this AD to 

detect and correct chafed hydraulic 

tubes in the left-hand engine and 

consequent hydraulic tube failure and 

uncontrolled loss of flammable fluid 

within the engine cowling, which could 

result in a fire in the engine nacelle and 

loss of control of the airplane. 

DATES: We must receive comments on 

this proposed AD by October 7, 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 W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Learjet, Inc., 

One Learjet Way, Wichita, Kansas 

67209–2942; telephone: 316–946–2000; 

fax: 316–946–2220; e-mail: 

ac.ict@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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

James Galstad, Aerospace Engineer, 

Systems and Propulsion Branch, ACE– 

116W, FAA, Wichita Aircraft 

Certification Office, 1801 Airport Road, 

Room 100, Mid-Continent Airport, 

Wichita, Kansas 67209; telephone (316) 

946–4135; fax (316) 946–4107. 

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–2010–0802; Directorate Identifier 

2009–NM–256–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

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. 


sroberts on DSKD5P82C1PROD with PROPOSALS
51702 Federal Register / Vol. 75, No. 162 / Monday, August 23, 2010 / Proposed Rules 

Discussion 

On May 20, 2009, we issued AD 

2009–11–13, amendment 39–15923 (74 

FR 26288, June 2, 2009), for certain 

Learjet Inc. Model 45 airplanes. That AD 

requires, for certain airplanes, repetitive 

inspections for chafing and other 

damage of the case drain tube from the 

hydraulic pump case installed on the 

left-hand engine, and corrective action if 

necessary. This AD also requires, for all 

airplanes, repetitive inspections for 

discrepancies of the left engine’s nacelle 

tubing, repetitive inspections for 

evidence of fluid leakage within the left 

engine accessory compartment, and 

corrective actions if necessary. That AD 

resulted from reports of chafed 

hydraulic tubes in the left-hand engine. 

We issued that AD to detect and correct 

chafed hydraulic tubes in the left-hand 

engine and consequent hydraulic tube 

failure and uncontrolled loss of 

flammable fluid within the engine 

cowling, which could result in a fire in 

the engine nacelle and loss of control of 

the airplane. 

Actions Since Existing AD Was Issued 

The preamble to AD 2009–11–13 

specifies that we consider the 

requirements ‘‘interim action’’ and that 

the manufacturer is developing a 

modification to address the unsafe 

condition. That AD explains that we 

might consider further rulemaking if a 

modification is developed, approved, 

and available. The manufacturer now 

has developed such a modification, and 

we have determined that further 

rulemaking is indeed necessary; this 

proposed AD follows from that 

determination. 

Changes to the Applicability 

The applicability of AD 2009–11–13 

includes airplanes having serial 

numbers (S/N) 45–002 through 45–4000 

inclusive. This proposed AD would 

apply to airplanes having S/Ns 45–005 

through 45–405 inclusive, and 45–2001 

through 45–2126 inclusive. Airplanes 

having S/Ns 45–406 through 45–2000 

and 45–2127 through 45–4000, have 

incorporated a design change in 

production that addresses the identified 

unsafe condition, and therefore we 

removed these airplanes from the 

applicability. We also removed S/N 45– 

002 because it is an experimental 

airplane at Learjet, and we removed S/ 

Ns 45–003 and 45–004 because they no 

longer exist. 

Relevant Service Information 

We have reviewed Bombardier 

Service Bulletins 40–71–04 (Model 45, 

serial numbers 45–2001 through 45– 

2126) and 45–71–7 (Model 45, serial 

numbers 45–005 through 45–405), both 

dated December 7, 2009. These service 

bulletins describe procedures for 

replacing the left engine fuel and 

hydraulic tubing and installing a tubing 

support channel, including doing a 

general visual inspection for galling of 

the fuel supply manifold assembly, a 

general visual inspection for minimum 

clearance between the firewall fuel 

supply tube assembly and the engine 

firewall cutout, a general visual 

inspection for minimum clearance 

between the lower nacelle hydraulic 

tube and hose assemblies, a general 

visual inspection for minimum 

clearance between the lower nacelle fuel 

tubes and flexible hoses, and corrective 

actions if necessary. The corrective 

actions include replacing the fuel 

supply manifold, trimming the cutout to 

meet minimum clearance specifications, 

and adjusting parts to meet minimum 

clearance specifications. Modification of 

the applicable in-service airplanes 

eliminates the need for the existing 

requirements of AD 2009–11–13. 

Bombardier Service Bulletin 45–71–7, 

dated December 7, 2009, specifies prior 

or concurrent accomplishment of 

Bombardier Service Bulletin 45–71–5, 

dated February 13, 2007, for airplanes 

having serial numbers 45–005 through 

45–319, and 45–321. Bombardier 

Service Bulletin 40–71–04, dated 

December 7, 2009, specifies prior or 

concurrent accomplishment of 

Bombardier Service Bulletin 40–71–02, 

dated February 13, 2007, for airplanes 

having serial numbers 45–2001 through 

45–2069. Bombardier Service Bulletins 

45–71–5 and 40–71–02, both dated 

February 13, 2007, describe the 

following procedures: 

• For certain airplanes, changing the 

routing and clamping configuration of 

the engine and alternator wire 

harnesses, and the starter/generator wire 

bundles. 

• For certain airplanes, doing a 

detailed inspection for chafing of 

specific hydraulic tubes located within 

the left engine nacelle between the 

adjacent fuel tubes and to determine if 

there is interference between the fuel 

tubing and hydraulic tubing, securing 

the hydraulic tubes with additional 

clamps, inspecting adjacent fuel tubing 

for interference with the hydraulic 

tubing, and corrective actions if 

necessary. Corrective actions include 

replacing chafed hydraulic tubes and 

replacing fuel tubes if interference is 

found. 

• For certain airplanes, replacing the 

left engine hydraulic pump case drain 

tube. 

• For certain airplanes, inspecting for 

clearance between the left engine 

hydraulic tubing with adjacent tubing, 

structure, and other components; and 

replacing tubing if necessary. 

• For all airplanes, inspecting for 

clearance between the wire harnesses 

and the hydraulic and fuel tubing on the 

left engines, if necessary; and replacing 

tubing if necessary. 

• For certain airplanes, inspecting for 

clearance between the wire harnesses 

and the hydraulic and fuel tubing on the 

right engines, if necessary; and 

replacing tubing if necessary. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to develop on 

other airplanes of the same type design. 

For this reason, we are proposing this 

AD, which would supersede AD 2009– 

11–13 and would retain the 

requirements of the existing AD until 

the modification is done. This proposed 

AD would also require accomplishing 

the actions specified in Bombardier 

Service Bulletins 40–71–04 and 45–71– 

7, both dated December 7, 2009; and 

Bombardier Service Bulletins 40–71–02 

and 45–71–5, both dated February 13, 

2007. 

Costs of Compliance 

There are about 530 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. 


sroberts on DSKD5P82C1PROD with PROPOSALS
Federal Register / Vol. 75, No. 162 / Monday, August 23, 2010 / Proposed Rules 51703 

ESTIMATED COSTS

Action Work 

hours 

Average 

labor rate 

per hour 

Parts Cost per 

airplane 

Number 

of U.S.- 

registered 

airplanes 

Fleet cost 

Inspection (required by AD 2009–11– 

13).

3 $85 $0 ........................ $255 per inspection.325 $82,875 per inspection. 

Modification (new proposed action) ... 20 85 Up to $14,740 ..... Up to $16,440 ..... 358 Up to $5,885,520. 

Concurrent Action .............................. 4 85 $189 .................... $529 .................... 358 $189,382. 

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 have 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 that the 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. See the ADDRESSES section 

for a location to examine the regulatory 

evaluation. 

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 

removing amendment 39–15923 (74 FR 

26288, June 2, 2009) and adding the 

following new AD: 

Learjet Inc.: Docket No. FAA–2010–0802; 

Directorate Identifier 2009–NM–256–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by October 7, 2010. 

Affected ADs 

(b) This AD supersedes AD 2009–11–13, 

Amendment 39–15923. 

Applicability 

(c) This AD applies to Learjet Inc. Model 

45 airplanes; certificated in any category; 

serial numbers 45–005 through 45–405 

inclusive, and 45–2001 through 45–2126 

inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 71: Powerplant. 

Unsafe Condition 

(e) This AD results from reports of chafed 

hydraulic tubes in the left-hand engine. The 

Federal Aviation Administration is issuing 

this AD to detect and correct chafed 

hydraulic tubes in the left-hand engine and 

consequent hydraulic tube failure and 

uncontrolled loss of flammable fluid within 

the engine cowling, which could result in a 

fire in the engine nacelle and loss of control 

of 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. 

Restatement of Requirements of AD 2009– 

11–13, With No Changes 

Repetitive Inspections: Case Drain Tube 

(g) For airplanes having serial numbers 

identified in Table 1 of this AD: Within 50 

flight hours after June 17, 2009 (the effective 

date of AD 2009–11–13), do a detailed 

inspection for chafing and other damage of 

the case drain tube from the hydraulic pump 

case installed on the left-hand engine, in 

accordance with the applicable service 

bulletin identified in Table 1 of this AD. If 

any damage is found, before further flight, 

reposition or replace the tube, as applicable, 

in accordance with the Accomplishment 

Instructions of the applicable service bulletin 

identified in Table 1 of this AD. Repeat the 

inspection thereafter at intervals not to 

exceed 150 flight hours until the 

modification required by paragraph (l) of this 

AD is done. 

TABLE 1—SERVICE BULLETINS FOR INSPECTIONS

For— Use— 

Serial numbers 45–005 through 45–313 inclusive (commonly referred 

to as ‘‘M45’’ airplanes).

Bombardier Alert Service Bulletin A45–29–15, dated December 26, 

2006. 

Serial numbers 45–2001 through 45–2063 inclusive (commonly referred to as ‘‘M40’’ airplanes).Bombardier Alert Service Bulletin A40–29–03, dated December 26, 

2006. 


sroberts on DSKD5P82C1PROD with PROPOSALS
51704 Federal Register / Vol. 75, No. 162 / Monday, August 23, 2010 / Proposed Rules 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’ 

Repetitive Inspections: Nacelle Tubing 

(h) Within 50 flight hours after June 17, 

2009, do a detailed inspection for 

discrepancies of the left engine’s nacelle 

tubing, in accordance with the applicable 

temporary revision (TR) identified in Table 2 

of this AD. Discrepancies include damaged 

tubing, and inadequate clearance between 

any unsupported section of the tube or other 

tubing and surrounding components. If any 

discrepancy is found, before further flight, 

adjust the tubing and clamping or replace the 

tubing, as applicable, in accordance with the 

applicable TR identified in Table 2 of this 

AD. Repeat the inspection thereafter at 

intervals not to exceed 150 flight hours until 

the modification required by paragraph (l) of 

this AD is done. 

TABLE 2—TRS FOR INSPECTIONS

For— Use— 

Serial numbers 45–2001 through 45–4000 inclusive (commonly referred to as ‘‘M40’’ airplanes).Learjet 40 TR 71–1, dated April 28, 2009, to the Learjet 40 Maintenance Manual MM–105. 

Serial numbers 45–002 through 45–2000 inclusive (commonly referred 

to as ‘‘M45’’ airplanes).

Learjet 45 TR 71–1, dated April 28, 2009, to the Learjet 45 Maintenance Manual MM–104. 

Concurrent Inspections: Fluid Leakage 

(i) Concurrently with each inspection 

required by paragraph (h) of this AD, do a 

detailed inspection for evidence of engine 

oil, hydraulic fluid, or fuel leakage within the 

left engine accessory compartment, in 

accordance with the applicable maintenance 

manual section identified in Table 3 of this 

AD. If there is evidence of leakage: Before 

further flight, remove each plumbing clamp 

within the inspection areas specified in 

paragraphs (g) and (h) of this AD, and clean 

and remove all evidence of fluid leakage. 

TABLE 3—MAINTENANCE MANUAL SECTIONS FOR INSPECTIONS

For— Use— 

Serial numbers 45–002 through 45–2000 inclusive (commonly referred 

to as ‘‘M45’’ airplanes).

Section 71–00–00, ‘‘Powerplant—Maintenance Practices,’’ and Section 

71–00–01, ‘‘Engine—Maintenance Practices,’’ of the Learjet 45 Maintenance Manual MM–104, Revision 47, dated March 30, 2009. 

Serial numbers 45–2001 through 45–4000 inclusive (commonly referred to as ‘‘M40’’ airplanes).Section 71–00–01, ‘‘Engine—Maintenance Practices,’’ of the Learjet 40 

Maintenance Manual MM–105, Revision 15, dated March 30, 2009. 

Additional Corrective Action for Fluid 

Leakage and Inadequate Clearance 

(j) If evidence of fluid leakage was found 

during any inspection required by paragraph 

(i) of this AD, or if inadequate clearance was 

found during any action required by 

paragraph (g) or (h) of this AD: Before further 

flight, replace each clamp associated with the 

fluid leakage or inadequate clearance with a 

new clamp, in accordance with the 

applicable maintenance manual identified in 

Table 3 of this AD. 

Parts Installation 

(k) As of June 17, 2009, no person may reinstall, on any airplane, any plumbing clamp 

that has been removed in accordance with 

the requirements of paragraphs (g), (h), (i), or 

(j) of this AD. 

New Requirements of This AD 

Terminating Action 

(l) Within 300 flight hours or 12 months 

after the effective date of this AD, whichever 

occurs first, do the actions specified in 

paragraphs (l)(1) and (l)(2) of this AD, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

40–71–04 (Model 45, serial numbers 45–2001 

through 45–2126) or 45–71–7 (Model 45, 

serial numbers 45–005 through 45–405), both 

dated December 7, 2009, as applicable. 

Accomplishment of the requirements of 

paragraphs (l) and (m), as applicable, of this 

AD terminates the requirements of 

paragraphs (g), (h), (i), and (j) of this AD. 

(1) Replace the left engine fuel and 

hydraulic tubing and install a tubing support 

channel using new parts. 

(2) Do the inspections specified in 

paragraphs (l)(2)(i), (l)(2)(ii), (l)(2)(iii), and 

(l)(2)(iv) of this AD and all applicable 

corrective actions. Do all applicable 

corrective actions before further flight. 

(i) A general visual inspection for galling 

of the fuel supply manifold assembly; 

(ii) A general visual inspection for 

minimum clearance between the firewall fuel 

supply tube assembly and the engine firewall 

cutout; 

(iii) A general visual inspection for 

minimum clearance between the lower 

nacelle hydraulic tube and hose assemblies; 

and 

(iv) A general visual inspection for 

minimum clearance between the lower 

nacelle fuel tubes and flexible hoses. 

(m) For airplanes having serial numbers 

45–005 through 45–319, and 45–321, as 

identified in Bombardier Service Bulletin 45– 

71–5, dated February 13, 2007; and for 

airplanes having serial numbers 45–2001 

through 45–2069, as identified in Bombardier 

Service Bulletin 40–71–02, dated February 

13, 2007: Before or concurrently with 

accomplishing the requirements of paragraph 

(l) of this AD, do the applicable actions 

specified in paragraphs (m)(1), (m)(2), (m)(3), 

(m)(4), and (m)(5) of this AD, depending on 

airplane serial number and configuration, as 

specified in, and in accordance with, the 

Accomplishment Instructions of Bombardier 

Service Bulletin 45–71–5 (Model 45, serial 

numbers 45–005 through 45–319, and 45– 

321), dated February 13, 2007; and 

Bombardier Service Bulletin 40–71–02 

(Model 45, serial numbers 45–2001 through 

45–2069), dated February 13, 2007; as 

applicable. Do all applicable corrective 

actions before further flight. If, during any 

inspection required by paragraph (m)(3), 

(m)(4), or (m)(5) of this AD, it is determined 

that clearances are not met, before further 

flight, replace the tubing in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 45–71–5, dated 

February 13, 2007; and Bombardier Service 

Bulletin 40–71–02, dated February 13, 2007; 

as applicable. 

(1) Change the routing and clamping 

configuration of the engine and alternator 

wire harnesses and the starter/generator wire 

bundles. 

(2) Do a detailed inspection for chafing 

damage of specific hydraulic tubes located 

within the left engine nacelle between the 

adjacent fuel tubes and to determine if there 

is interference between the fuel tubing and 

hydraulic tubing; secure hydraulic tubes with 

additional clamps, inspect adjacent fuel 

tubing for interference with the hydraulic 

tubing, replace the left engine hydraulic 

pump case drain tube on certain airplanes, 

and do all applicable corrective actions. 

(3) Do a general visual inspection for 

clearance between the left engine hydraulic 


sroberts on DSKD5P82C1PROD with PROPOSALS
Federal Register / Vol. 75, No. 162 / Monday, August 23, 2010 / Proposed Rules 51705 

tubing with adjacent tubing, structure, and 

other components. 

(4) Do a general visual inspection for 

clearance between the wire harnesses and the 

hydraulic and fuel tubing on the left engine. 

(5) Do a general visual inspection for 

clearance between the wire harnesses and the 

hydraulic and fuel tubing on the right engine. 

Alternative Methods of Compliance 

(AMOCs) 

(n)(1) The Manager, Wichita 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: James 

Galstad, Aerospace Engineer, Systems and 

Propulsion Branch, ACE–116W, FAA, 

Wichita ACO, 1801 Airport Road, Room 100, 

Mid-Continent Airport, Wichita, Kansas 

67209; telephone (316) 946–4135; fax (316) 

946–4107. 

(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) AMOCs approved previously in 

accordance with AD 2009–11–13, 

amendment 39–15923, are approved as 

AMOCs for the corresponding provisions of 

this AD. 

Issued in Renton, Washington, on August 

16, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–20853 Filed 8–20–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0801; Directorate 

Identifier 2010–NM–054–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600 and A300 B4–600R Series 

Airplanes, Model A300 F4–605R 

Airplanes, and Model A300 C4–605R 

Variant F 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: A recent Widespread 

Fatigue Damage (WFD) calculation on 

A300–600 aeroplanes has shown that a 

reinforcement of the upper fuselage 

circumferential joint at FR (frame) 58 is 

necessary to enable the aeroplane to 

reach the Extended Service Goal (ESG). 

The failure of the circumferential joint 

of the upper fuselage could affect the 

structural integrity of the aeroplane. 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 7, 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 Airbus SAS– 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax: +33 5 61 93 44 51; e-mail: 

account.airworth-eas@airbus.com; 

Internet: http://www.airbus.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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; 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–2010–0801; Directorate Identifier 

2010–NM–054–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 2010–0007, 

dated January 7, 2010 (referred to after 

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

condition for the specified products. 

The MCAI states: 

A recent Widespread Fatigue Damage 

(WFD) calculation on A300–600 aeroplanes 

has shown that a reinforcement of the upper 

fuselage circumferential joint at FR (frame) 

58 is necessary to enable the aeroplane to 

reach the Extended Service Goal (ESG). 

The failure of the circumferential joint of 

the upper fuselage could affect the structural 

integrity of the aeroplane. 

For the reasons described above, this AD 

requires the reinforcement of the affected 

fuselage frame butt joint. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A300–53–6146, Revision 01, 


sroberts on DSKD5P82C1PROD with PROPOSALS