Federal Register / Vol. 78, No. 156 / Tuesday, August 13, 2013 / Proposed Rules 49229 

Bombardier, Inc.: Docket No. FAA–2013– 

0687; Directorate Identifier 2012–NM– 

118–AD. 

(a) Comments Due Date 

We must receive comments by September 

27, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Bombardier, Inc. 

Model CL–600–2B19 (Regional Jet Series 100 

& 440) airplanes, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by reports of burr 

marks on the primary wheels, and cracked 

rings on the primary wheel shaft, on certain 

HSTAs. We are issuing this AD to prevent 

burr marks on the primary wheels, and 

cracked rings on the primary wheel shaft, on 

certain HSTAs, which may lead to a 

disconnect of the pitch trim surface and 

subsequent loss of pitch control, resulting in 

loss of control of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspection 

Within 1,000 flight hours or 4 months after 

the effective date of this AD, whichever 

occurs first, inspect to determine if any 

HSTA having part number (P/N) 601R92305– 

5 or vendor P/N 8396–4, with serial numbers 

(S/N)s 287, 724, 813, 841, 998, 1031, 1035, 

1049, 1053, 1067, 1068, 1136, 1252, 1268, 

1303, 1319, 1338, 1354, 1374, 1378, 1445, 

1470, 1498, 1513, 1546, 1632, 1736, 1766, 

1846, 1849, 2002 through 2009, 2011, 2013 

through 2016, 2019, 2020, and 2022 is 

installed. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the part number of the HSTA 

can be conclusively determined from that 

review. 

(h) Replacement 

Within 1,000 flight hours or 4 months after 

the effective date of this AD, whichever 

occurs first, replace the affected HSTAs 

identified in paragraph (g) of this AD, with 

a serviceable HSTA, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–27–159, dated June 15, 

2011. 

(i) Parts Installation Limitations 

As of the effective date of this AD, no 

person may install any HSTA having P/N 

601R92305–5 or vendor P/N 8396–4 with a 

S/N listed in paragraph (g) of this AD, unless 

the S/N has the suffix ‘‘A’’ beside it. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office, (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information Canadian 

Airworthiness Directive CF–2012–18, dated 

May 29, 2012, for related information, which 

can be found in the AD docket on the 

internet at http://www.regulations.gov. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email 

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, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on August 

6, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19534 Filed 8–12–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0690; Directorate 

Identifier 2013–NM–088–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2009–24– 

07, which applies to certain The Boeing 

Company Model 737–600, –700, –700C, 

and –800 series airplanes. AD 2009–24– 

07 currently requires repetitive 

lubrications of the right and left main 

landing gear (MLG) forward trunnion 

pins. AD 2009–24–07 also requires an 

inspection for discrepancies of the 

transition radius of the MLG forward 

trunnion pins, and corrective actions if 

necessary. For certain airplanes, AD 

2009–24–07 requires repetitive detailed 

inspections for discrepancies (including 

finish damage, corrosion, pitting, and 

base metal scratches) of the transition 

radius of the left and right MLG 

trunnion pins, and corrective action if 

necessary. Replacing or overhauling the 

trunnion pins would terminate the 

actions required by AD 2009–24–07. 

This proposed AD would add airplanes 

to the applicability of AD 2009–24–07. 

We are proposing this AD to prevent 

stress corrosion cracking of the forward 

trunnion pins, which could result in 

fracture of the pins and consequent 

collapse of the MLG. 

DATES: We must receive comments on 

this proposed AD by September 27, 

2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https:// 

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, Washington 98057–3356. 

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:// 


ehiers on DSK2VPTVN1PROD with PROPOSALS-1
49230 Federal Register / Vol. 78, No. 156 / Tuesday, August 13, 2013 / Proposed Rules 

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 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone 425– 

917–6440; fax 425–917–6590; email: 

nancy.marsh@faa.gov. 

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–2013–0690; Directorate Identifier 

2013–NM–088–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. 

Discussion 

On November 12, 2009, we issued AD 

2009–24–07, Amendment 39–16095 (74 

FR 62231, November 27, 2009), for 

certain Model 737–600, –700, –700C, 

and –800 series airplanes. AD 2009–24– 

07 requires repetitive lubrications of the 

right and left main landing gear (MLG) 

forward trunnion pins. AD 2009–24–07 

also requires an inspection for 

discrepancies of the transition radius of 

the MLG forward trunnion pins, and 

corrective actions if necessary. For 

certain airplanes, AD 2009–24–07 also 

requires repetitive detailed inspections 

for discrepancies (including finish 

damage, corrosion, pitting, and base 

metal scratches) of the transition radius 

of the left and right MLG trunnion pins, 

and corrective action if necessary. 

Replacing or overhauling the trunnion 

pins would terminate the actions 

required by that AD. AD 2009–24–07 

resulted from a report that the protective 

finishes on the forward trunnion pins 

for the left and right MLG might have 

been damaged during final assembly. 

We issued AD 2009–24–07 to prevent 

stress corrosion cracking of the forward 

trunnion pins, which could result in 

fracture of the pins and consequent 

collapse of the MLG. 

Actions Since AD 2009–24–07 Was 

Issued 

Since we issued AD 2009–24–07, we 

have determined that airplanes outside 

the applicability of AD 2009–24–07, 

including Model 737–900 airplanes, are 

also subject to the identified unsafe 

condition. This determination is due to 

reports of corrosion protection damage 

to the forward trunnion pin on some of 

those airplanes. 

Relevant Service Information 

We reviewed Boeing Special 

Attention Service Bulletin 737–32– 

1402, Revision 1, dated February 7, 

2013. For information on the procedures 

and compliance times, see this service 

information at http:// 

www.regulations.gov by searching for 

Docket No. FAA–2013–0690. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

Although this proposed AD does not 

explicitly restate the requirements of AD 

2009–24–07, this proposed AD would 

retain all of the requirements of AD 

2009–24–07. Those requirements are 

referenced in the service information 

identified previously, which, in turn, is 

referenced in paragraphs (g), (h), and (i) 

of this proposed AD. This proposed AD 

would also add airplanes to the 

applicability statement of AD 2009–24– 

07. This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ are actions that correct or 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 431 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per product 

Number of 

U.S.-registered airplanes 

Fleet cost 

Repetitive lubrications ....... 1 $85 $0 $85 per lubrication ............ 431 $8,500 per lubrication. 

Repetitive inspections ........ 8 85 0 $680 per inspection cycle 431 $68,000 per inspection 

cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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. 


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Federal Register / Vol. 78, No. 156 / Tuesday, August 13, 2013 / Proposed Rules 49231 

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), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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. 

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 airworthiness directive (AD) 

2009–24–07, Amendment 39–16095 (74 

FR 62231, November 27, 2009), and 

adding the following new AD: 

The Boeing Company: Docket No. FAA– 

2013–0690; Directorate Identifier 2013– 

NM–088–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by September 27, 2013. 

(b) Affected ADs 

This AD supersedes AD 2009–24–07, 

Amendment 39–16095 (74 FR 62231, 

November 27, 2009). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–600, –700, –700C, –800 and –900 

series airplanes, certificated in any category; 

as identified in Boeing Special Attention 

Service Bulletin 737–32–1402, Revision 1, 

dated February 7, 2013. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 32, Landing gear. 

(e) Unsafe Condition 

This AD was prompted by a report that the 

protective finishes on the forward trunnion 

pins for the left and right MLG might have 

been damaged during final assembly. We are 

issuing this AD to prevent stress corrosion 

cracking of the forward trunnion pins, which 

could result in fracture of the pins and 

consequent collapse of the MLG. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Lubrications 

At the applicable compliance time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

737–32–1402, Revision 1, dated February 7, 

2013, except as required by paragraph (j) of 

this AD: Lubricate the left and right MLG 

forward trunnion pins, in accordance with 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–32– 

1402, Revision 1, dated February 7, 2013. 

Repeat the lubrication thereafter at the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ until all applicable 

requirements of paragraph (h) of this AD 

have been accomplished. 

(h) Inspection 

At the applicable compliance time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

737–32–1402, Revision 1, dated February 7, 

2013, except as required by paragraph (j) of 

this AD: Except as provided by paragraph (i) 

of this AD, do a detailed inspection for 

discrepancies (including finish damage, 

corrosion, pitting, and base metal scratches) 

of the transition radius of the left and right 

MLG trunnion pins, and do all applicable 

repetitive inspections and related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–32–1402, Revision 1, 

dated February 7, 2013. Accomplishing the 

detailed inspections (initial and repetitive) 

and all applicable corrective actions 

specified in this paragraph terminates the 

repetitive lubrication requirements of 

paragraph (g) of this AD. 

(i) Optional Terminating Action 

Overhauling or replacing a trunnion pin in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–32–1402, Revision 1, 

dated February 7, 2013, ends the repetitive 

lubrication requirements of paragraph (g) of 

this AD, and the actions required by 

paragraph (h) of this AD, for that pin only. 

(j) Exception to Service Information 

Specifications 

Where Boeing Special Attention Service 

Bulletin 737–32–1402, Revision 1, dated 

February 7, 2013, specifies a compliance time 

‘‘from the date of Revision 1 of this service 

bulletin,’’ this AD requires compliance 

within the specified compliance time after 

the effective date of this AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by this AD, if those actions 

were performed before the effective date of 

this AD using Boeing Special Attention 

Service Bulletin 737–32–1402, dated August 

6, 2008. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes ODA that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 2009–24–07, 

Amendment 39–16095 (74 FR 62231, 

November 27, 2009), are approved as AMOCs 

for the corresponding actions required by 

paragraphs (g) and (h) of this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone 425–917–6440; fax 425–917– 

6590; email: nancy.marsh@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com.You 

may review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356. For information on 

the availability of this material at the FAA, 

call 425–227–1221. You may review copies 

of the referenced service information at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington 

98057–3356. For information on the 

availability of this material at the FAA, call 

425–227–1221. 


ehiers on DSK2VPTVN1PROD with PROPOSALS-1
49232 Federal Register / Vol. 78, No. 156 / Tuesday, August 13, 2013 / Proposed Rules 

Issued in Renton, Washington, on August 

2, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19531 Filed 8–12–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0691; Directorate 

Identifier 2012–NM–170–AD] 

RIN 2120–AA64 

Airworthiness Directives; Learjet Inc. 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain Learjet Inc. Model 

60 airplanes. The existing AD currently 

requires determining if a certain fuel 

crossflow tube is installed; and followon/corrective actions, as applicable. 

Since we issued that AD, we have 

received a report that airplanes 

produced since 2003 might also be 

subject to the unsafe condition; and that 

the minimum allowable clearance is not 

established in the airplane maintenance 

information, and therefore, must be 

addressed by this proposed AD. This 

proposed AD would retain all actions in 

the previous AD, and would require 

determining if a certain fuel crossflow 

tube is installed, performing repetitive 

measurements of the fuel crossflow tube 

and surrounding valves and cables, and 

doing corrective actions if applicable. In 

addition, this proposed AD expands the 

applicability of the existing AD. We are 

proposing this AD to prevent chafing 

and consequent failure of the fuel 

crossflow tube due to inadequate 

clearance between the tube and the 

flight control cables, which could result 

in loss of fuel from one fuel tank during 

normal operating conditions or loss of 

fuel from both main fuel tanks during 

fuel cross-feeding operations. 

DATES: We must receive comments on 

this proposed AD by September 27, 

2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Learjet, Inc., One 

Learjet Way, Wichita, KS 67209–2942; 

telephone 316–946–2000; fax 316–946– 

2220; email 

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, WA. 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 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Jeff 

Janusz, Aerospace Engineer, Propulsion 

Branch, ACE–116W, FAA, Wichita 

Aircraft Certification Office (ACO), 1801 

Airport Road, Room 100, Wichita, 

Kansas 67209; phone: 316–946–4148; 

fax: 316–946–4107; email: 

jeff.janusz@faa.gov. 

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–2013–0691; Directorate Identifier 

2012–NM–170–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. 

Discussion 

On September 16, 2003, we issued AD 

2003–19–11, Amendment 39–13314 (68 

FR 55812, September 29, 2003), for 

certain Learjet Inc. Model 60 airplanes. 

That AD requires a review of airplane 

maintenance records or an inspection to 

determine if a fuel crossflow tube 

having a certain part number is 

installed; and follow-on/corrective 

actions, as applicable. That AD resulted 

from reports of chafing of the fuel 

crossflow tube by flight control cables. 

We issued that AD to prevent chafing 

and consequent failure of the fuel 

crossflow tube due to inadequate 

clearance between the tube and the 

flight control cables, which could result 

in loss of fuel from one fuel tank during 

normal operating conditions or loss of 

fuel from both main fuel tanks during 

fuel cross-feeding operations. 

Actions Since Existing AD 2003–19–11, 

Amendment 39–13314 (68 FR 55812, 

September 29, 2003) Was Issued 

Since we issued AD 2003–19–11, 

Amendment 39–13314 (68 FR 55812, 

September 29, 2003), we have received 

a report that airplanes produced since 

2003 might be subject to the unsafe 

condition; and that the minimum 

allowable clearance is not established in 

the airplane maintenance information, 

and therefore, must be addressed by this 

proposed AD. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would retain all 

requirements of AD 2003–19–11, 

Amendment 39–13314 (68 FR 55812, 

September 29, 2003). This proposed AD 

would retain all actions in the previous 

AD, and would require determining if a 

certain fuel crossflow tube is installed, 

performing repetitive measurements of 

the fuel crossflow tube and surrounding 

valve and cables, and doing corrective 

actions if applicable. 


ehiers on DSK2VPTVN1PROD with PROPOSALS-1