Federal Register / Vol. 76, No. 131 / Friday, July 8, 2011 / Proposed Rules 40291 

paragraph, before further flight, repair in 

accordance with a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(2) If any crack that is two inches or less 

is found in the rear spar upper cap, do the 

actions specified in paragraph (i)(2)(i) or 

(i)(2)(ii) of this AD. 

(i) Option 1: Do the actions specified in 

paragraphs (i)(2)(i)(A), (i)(2)(i)(B), and 

(i)(2)(i)(C) of this AD. 

(A) Before further flight, do a doubler 

repair of the rear spar upper cap and a splice 

repair of the rear spar lower cap, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–57A026, Revision 1, dated February 

23, 2011. 

(B) Within 13,500 flight cycles after doing 

the doubler repair required by paragraph 

(i)(2)(i)(A) of this AD, do an ETHF inspection 

for any cracking in the repaired area of the 

rear spar upper cap, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD90–57A026, Revision 1, 

dated February 23, 2011. Repeat the 

inspection thereafter at intervals not to 

exceed 8,500 flight cycles. If any cracking is 

found during any inspection required by this 

paragraph, before further flight, repair in 

accordance with a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(C) Within 20,000 flight cycles after doing 

the splice repair required by paragraph 

(i)(2)(i)(A) of this AD, do an ETLF and a UT 

inspection for cracking in the repaired area 

of the rear spar lower cap, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin MD90–57A026, 

Revision 1, dated February 23, 2011. Repeat 

the inspections thereafter at intervals not to 

exceed 3,000 flight cycles. If any cracking is 

found during any inspection required by this 

paragraph, before further flight, repair in 

accordance with a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(ii) Option 2: Before further flight, do a 

splice repair of the rear spar upper and lower 

caps, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD90–57A026, Revision 1, 

dated February 23, 2011. Within 20,000 flight 

cycles after doing the splice repair, do an 

ETLF and a UT inspection for cracking in the 

repaired area of the rear spar lower cap, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–57A026, Revision 1, dated February 

23, 2011. Repeat the inspections thereafter at 

intervals not to exceed 3,000 flight cycles. If 

any cracking is found during any inspection 

required by this paragraph, before further 

flight, repair in accordance with a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD. 

(3) If any crack that is greater than two 

inches is found in the rear spar upper cap, 

before further flight, do a splice repair of the 

rear spar upper and lower caps, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–57A026, Revision 1, dated February 

23, 2011. Within 20,000 flight cycles after 

doing the splice repair, do an ETLF and a UT 

inspection for cracking in the repaired area 

of the rear spar lower cap, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin MD90–57A026, 

Revision 1, dated February 23, 2011. Repeat 

the inspections thereafter at intervals not to 

exceed 3,000 flight cycles. If any cracking is 

found during any inspection required by this 

paragraph, before further flight, repair in 

accordance with a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(j) Doing an ETHF inspection for cracks, 

and doing a doubler repair to the rear spar 

upper and lower caps in accordance with 

Boeing Alert Service Bulletin MD90–57A026, 

dated February 11, 2010, before the effective 

date of this AD, are acceptable for 

compliance with the corresponding actions 

required by paragraphs (g), (h), and (i) of this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Los Angeles 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. 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. 

(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 Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

Related Information 

(l) For more information about this AD, 

contact Roger Durbin, Airframe Branch, 

ANM–120L, FAA, Los Angeles ACO, 3960 

Paramount Boulevard, Lakewood, California 

90712–4137; phone: (562) 627–5233; fax: 

(562) 627–5210; e-mail: 

roger.durbin@faa.gov. 

(m) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, California 90846– 

0001; telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.boecom@boeing.com; 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. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on June 29, 

2011. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–17267 Filed 7–7–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0651; Directorate 

Identifier 2011–NM–041–AD] 

RIN 2120–AA64 

Airworthiness Directives; Learjet Inc. 

Model 45 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 would require revising the 

maintenance program to incorporate life 

limits for the main landing gear (MLG) 

actuator end cap. This proposed AD was 

prompted by a report of the potential for 

fatigue cracking of the end cap of the 

MLG prior to the published life 

limitation. We are proposing this AD to 

prevent fatigue cracking of the end cap 

of the MLG, which could result in the 

failure of the MLG actuator upon 

landing, and failure of the MLG to 

extend or retract during flight. 

DATES: We must receive comments on 

this proposed AD by August 22, 2011. 

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: 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 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 


jlentini on DSK4TPTVN1PROD with PROPOSALS
40292 Federal Register / Vol. 76, No. 131 / Friday, July 8, 2011 / Proposed Rules 

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 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Paul 

Chapman, Aerospace Engineer, Aviation 

Safety, ACE–118W, FAA, Wichita 

Aircraft Certification Office, 1801 

Airport Road, Room 100, Mid-Continent 

Airport, Wichita, KS 67209; phone: 

316–946–4152; fax: 316–946–4107; 

e-mail: paul.chapman@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2011–0651; Directorate Identifier 2011– 

NM–041–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 

We received a report from Learjet that 

indicated the life limitation of the main 

landing gear actuator was determined 

using fatigue testing during the Model 

45 certification; however, the supplier 

discovered they had not tested the 

actuator properly during subsequent 

testing for another application. Learjet 

identified the potential for fatigue 

cracking of the end cap of the main 

landing gear actuator prior to the 

published life limitation. This potential 

for fatigue cracking, if not corrected, 

could result in failure of the main 

landing gear actuator upon landing, and 

failure of the MLG to extend or retract 

during flight. 

Relevant Service Information 

We reviewed Learjet 40 Temporary 

Revision 4–23, dated January 24, 2011, 

to Learjet 40 Maintenance Manual MM– 

105; and Learjet 45 Temporary Revision 

4–34, dated January 24, 2011, to Learjet 

45 Maintenance Manual MM–104. 

Among other things, the Airworthiness 

Limitations sections contained in 

Learjet 40 Temporary Revision 4–23 and 

Learjet 45 Temporary Revision 4–34 

provide new life limits and replacement 

compliance times for the MLG actuator 

end cap. 

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 these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require 

revising the maintenance program to 

incorporate life limits for the MLG 

actuator end cap. 

Costs of Compliance 

We estimate that this proposed AD 

affects 351 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Revise maintenance plan ......... 1 work-hour × $85 per hour = $85 per revision.$0 $85 per revision ...................... $29,835 

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), 

(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: 


jlentini on DSK4TPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 131 / Friday, July 8, 2011 / Proposed Rules 40293 

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 airworthiness 

directive (AD): 

Learjet Inc.: Docket No. FAA–2011–0651; 

Directorate Identifier 2011–NM–041–AD. 

Comments Due Date 

(a) We must receive comments by August 

22, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Learjet Inc. Model 

45 airplanes, certificated in any category; all 

serial numbers. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new actions (e.g. inspections). 

Compliance with these actions is required by 

14 CFR 91.403(c). For airplanes that have 

been previously modified, altered, or 

repaired in the areas addressed by these 

actions, the operator may not be able to 

accomplish the actions described in the 

revisions. In this situation, to comply with 14 

CFR 91.403(c), the operator must request 

approval for an alternative method of 

compliance according to paragraph (i) of this 

AD. The request should include a description 

of changes to the required actions that will 

ensure the continued operational safety of 

the airplane. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing Gear. 

Unsafe Condition 

(e) This AD was prompted by a report of 

the potential for fatigue cracking of the end 

cap of the main landing gear (MLG) prior to 

the published life limitation. We are issuing 

this AD to prevent fatigue cracking of the end 

cap of the MLG, which could result in the 

failure of the MLG actuator upon landing, 

and failure of the MLG to extend or retract 

during flight. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Maintenance Program Revision 

(g) Within 30 days after the effective date 

of this AD, revise the maintenance program 

by incorporating IRN T3220105 (Main 

Landing Gear Actuator End Cap (P/N 200– 

0303)) as specified in Learjet 40 Temporary 

Revision 4–23, dated January 24, 2011, to 

Learjet 40 Maintenance Manual MM–105; or 

Learjet 45 Temporary Revision 4–34, dated 

January 24, 2011, to Learjet 45 Maintenance 

Manual MM–104; as applicable. The initial 

compliance for the replacement specified in 

IRN T3220105 is prior to the accumulation of 

2,387 total flight cycles on the end cap (P/ 

N 200–0303), or within 25 flight cycles after 

the effective date of this AD, whichever 

occurs later. 

No Alternative Actions or Intervals 

(h) After accomplishing the revision 

required by paragraph (g) of this AD, no 

alternative actions (e.g., replacements) or 

intervals, may be used, unless the actions or 

intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (i) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(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. 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. 

(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. The AMOC 

approval letter must specifically reference 

this AD. 

Related Information 

(j) For more information about this AD, 

contact Paul Chapman, Aerospace Engineer, 

Aviation Safety, ACE–118W, FAA, Wichita 

Aircraft Certification Office, 1801 Airport 

Road, Room 100, Mid-Continent Airport, 

Wichita, KS 67209; phone: 316–946–4152; 

fax: 316–946–4107; e-mail: 

paul.chapman@faa.gov. 

(k) For service information identified in 

this 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. 

Issued in Renton, Washington, on June 29, 

2011. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–17265 Filed 7–7–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2011–0425; Airspace 

Docket No. 11–ANM–9] 

Proposed Amendment of Class D and 

Modification of Class E Airspace; 

Grand Junction, CO 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

modify Class E airspace at Grand 

Junction Regional Airport, Grand 

Junction, CO. Additional controlled 

airspace is necessary to facilitate 

vectoring of Instrument Flight Rules 

(IFR) traffic from Grand Junction 

Regional Airport to en route. The FAA 

is proposing this action to enhance the 

safety and management of aircraft 

operations at Grand Junction Regional 

Airport. This action also would amend 

Class D and Class E airspace to update 

the airport name from Grand Junction, 

Walker Field. 

DATES: Comments must be received on 

or before August 22, 2011. 

ADDRESSES: Send comments on this 

proposal to the U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590; telephone (202) 

366–9826. You must identify FAA 

Docket No. FAA–2011–0425; Airspace 

Docket No. 11–ANM–9, at the beginning 

of your comments. You may also submit 

comments through the Internet at http:// 

www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: 

Eldon Taylor, Federal Aviation 

Administration, Operations Support 

Group, Western Service Center, 1601 

Lind Avenue, SW., Renton, WA 98057; 

telephone (425) 203–4537. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested parties are invited to 

participate in this proposed rulemaking 

by submitting such written data, views, 

or arguments, as they may desire. 

Comments that provide the factual basis 

supporting the views and suggestions 

presented are particularly helpful in 

developing reasoned regulatory 

decisions on the proposal. Comments 

are specifically invited on the overall 

regulatory, aeronautical, economic, 

environmental, and energy-related 

aspects of the proposal. 


jlentini on DSK4TPTVN1PROD with PROPOSALS