Federal Register / Vol. 78, No. 127 / Tuesday, July 2, 2013 / Rules and Regulations 39571 

Directorate, 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 International Branch, send it to ATTN: 

Cindy Ashforth, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–2768; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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. 

(3) AMOCs approved previously in 

accordance with AD 2010–14–14, 

Amendment 39–16359 (75 FR 42585, July 22, 

2010), are not approved as AMOCs for this 

AD. 

(r) Related Information 

(1) Refer to MCAI Brazilian Airworthiness 

Directive 2005–09–03R3, effective May 30, 

2011 (http://www2.anac.gov.br/certificacao/ 

da/Textos/1336amd.pdf); Brazilian 

Airworthiness Directive 2006–11–01R6, 

effective May 30, 2011 (http:// 

www2.anac.gov.br/certificacao/DA/Textos/ 

1337amd.pdf); for related information. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD may be obtained at the addresses 

specified in paragraphs (s)(7) and (s)(8) of 

this AD. 

(s) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on August 6, 2013. 

(i) EMBRAER Service Bulletin 190LIN–36– 

0004, dated December 23, 2009. 

(ii) Task 36–11–02–002 (Low Stage Bleed 

Check Valve) specified in Section 1 of the 

EMBRAER 170 Maintenance Review Board 

Report (MRBR), MRB–1621, Revision 7, 

dated November 11, 2010. 

(4) The following service information was 

approved for IBR on August 26, 2010 (75 FR 

42585, July 22, 2010). 

(i) EMBRAER Service Bulletin 170–36– 

0004, Revision 01, dated March 10, 2008. 

(ii) EMBRAER Service Bulletin 170–36– 

0011, Revision 02, dated July 19, 2007. 

(iii) EMBRAER Service Bulletin 190–36– 

0006, Revision 01, dated July 19, 2007. 

(iv) EMBRAER Service Bulletin 190–36– 

0014, Revision 01, dated January 14, 2009. 

(v) Task 36–11–02–002 (Low Stage Bleed 

Check Valve) specified in Section 1 of the 

EMBRAER 170 MRBR MRB–1621, Revision 

6, dated January 14, 2010. 

(5) The following service information was 

approved for IBR on September 13, 2007 (72 

FR 44734, August 9, 2007). 

(i) EMBRAER Service Bulletin 170–36– 

0004, dated November 18, 2005. 

(ii) Reserved. 

(6) The following service information was 

approved for IBR on November 29, 2005 (70 

FR 69075, November 14, 2005). 

(i) EMBRAER Alert Service Bulletin 170– 

36–A004, dated September 28, 2005. 

(ii) Reserved. 

(7) For service information identified in 

this AD, contact Embraer S.A., Technical 

Publications Section (PC 060), Av. Brigadeiro 

Faria Lima, 2170—Putim—12227–901 Sa ̃o 

Jose dos Campos–SP—BRASIL; telephone 

+55 12 3927–5852 or +55 12 3309–0732; fax 

+55 12 3927–7546; email 

distrib@embraer.com.br; Internet http:// 

www.flyembraer.com. 

(8) You may review copies of the 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. 

(9) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on May 29, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–15637 Filed 7–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0620; Directorate 

Identifier 2007–NM–357–AD; Amendment 

39–17499; AD 2013–13–11] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 747–400, 

–400D, and –400F series airplanes. This 

AD was prompted by reports of two inservice occurrences on Model 737–400 

airplanes of total loss of boost pump 

pressure of the fuel feed system, 

followed by loss of fuel system suction 

feed capability on one engine, and inflight shutdown of the engine. This AD 

requires repetitive operational tests of 

the engine fuel suction feed of the fuel 

system, and other related testing and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

loss of the engine fuel suction feed 

capability of the fuel system, which, in 

the event of total loss of the fuel boost 

pumps, could result in multi-engine 

flameout, inability to restart the engines, 

and consequent forced landing of the 

airplane. 

DATES: This AD is effective August 6, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 6, 2013. 

ADDRESSES: 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. 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Sue 

Lucier, Aerospace Engineer, Propulsion 

Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 

98057–3356; phone: 425–917–6438; fax: 

425–917–6590; email: 

suzanne.lucier@faa.gov. 

SUPPLEMENTARY INFORMATION: 


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39572 Federal Register / Vol. 78, No. 127 / Tuesday, July 2, 2013 / Rules and Regulations 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to include an 

airworthiness directive (AD) that would 

apply to the specified products. That 

SNPRM published in the Federal 

Register on July 9, 2012 (77 FR 40307). 

The original NPRM (73 FR 32248, June 

6, 2008) proposed to require repetitive 

operational tests of the engine fuel 

suction feed of the fuel system, and 

other related testing if necessary. The 

SNPRM proposed to require repetitive 

operational tests and corrective actions 

if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 40307, 

July 9, 2012) and the FAA’s response to 

each comment. Boeing reviewed the 

SNPRM and concurs with the content. 

Request To Change the Compliance 

Time for the Operational Tests 

United Airlines (UAL) asked that we 

change the compliance times for the 

operational test in the SNPRM (77 FR 

40307, July 9, 2012) from 30,000 flight 

hours after the effective date of the AD 

to ‘‘within 30,000 flight hours or 72 

months after the effective date of the 

proposed AD, whichever is later.’’ UAL 

also asked that the repetitive interval be 

changed to ‘‘intervals not to exceed 

30,000 flight hours or 72 months.’’ UAL 

stated that, ‘‘ . . . Boeing 747–400 MRB 

No. 28–022–04 requires the initial and 

repeat operational tests be performed at 

1D [maintenance] interval.’’ UAL added 

that the suggested change would 

provide an acceptable level of safety and 

provide operators some degree of 

flexibility in scheduling the required 

task. 

We do not agree with the request to 

change the compliance time proposed in 

the SNPRM (77 FR 40307, July 9, 2012). 

Boeing Alert Service Bulletin 747– 

28A2330, dated April 2, 2012, has been 

revised to change the compliance time 

and clarify certain procedures in the 

Work Instructions. We reviewed Boeing 

Service Bulletin 747–28A2330, Revision 

1, dated November 30, 2012, and we are 

not mandating the newly recommended 

compliance time in this AD; however, 

we are including Boeing Service 

Bulletin 747–28A2330, Revision 1, 

dated November 30, 2012, in paragraph 

(g) of this AD as an option to using the 

original issue of this service information 

for procedures to accomplish the 

required actions. 

We partially agree with including a 

compliance time for low-utilization 

airplanes; however, adding a calendar 

time of 72 months would constitute a 

more restrictive compliance time and 

would necessitate issuing another 

supplemental NPRM, which would 

delay issuance of this final rule. We 

determined that the compliance time of 

‘‘within 30,000 flight hours or 6 years, 

whichever is first,’’ as stated in Boeing 

Service Bulletin 747–28A2330, Revision 

1, dated November 30, 2012, was 

changed to address low-utilization 

airplanes and will adequately address 

the unsafe condition identified. 

Therefore, we have not changed the AD 

in this regard. 

Request To Correct Errors in Service 

Information 

UAL asked that a service bulletin 

information notice (IN) be issued to 

address two errors in Boeing Alert 

Service Bulletin 747–28A2330, dated 

April 2, 2012. UAL noted that the first 

error is the reserve tank identifications, 

and the second error is an airplane 

maintenance manual (AMM) procedure 

referred to in the Work Instructions that 

is not identified in UAL’s AMM. UAL 

stated that issuing an IN would prevent 

alternative method of compliance 

(AMOC) requests from operators. 

We acknowledge and agree with the 

commenter’s concern. As noted 

previously, we reviewed Boeing Service 

Bulletin 747–28A2330, Revision 1, 

dated November 30, 2012, which 

clarifies the reserve tank identifications. 

We have added this service information 

as an option for accomplishing the 

actions required by paragraph (g) of this 

AD. However, the second error 

identified by UAL involves the 

instructions in operator-customized 

maintenance manuals published by 

Boeing. Therefore, UAL should contact 

Boeing for resolution of the missing 

procedure in its AMM. Operators need 

not request AMOC approvals to use 

Boeing Alert Service Bulletin 747– 

28A2330, dated April 2, 2012, with 

regard to these errors since compliance 

is not affected. 

Request to Allow Alternative 

Procedures for Performing Operational 

Test 

UAL asked that paragraph (g) of the 

SNPRM (77 FR 40307, July 9, 2012) be 

changed to allow alternative procedures 

for performing the operational test 

instead of using the procedures 

provided in Boeing Alert Service 

Bulletin 747–28A2330, dated April 2, 

2012. UAL stated that an alternative test 

is specified in the Boeing Model 747– 

400 AMM 28–22–00, Task 28–22–00– 

710–801, titled ‘‘Engine Fuel Suction 

Feed—Operational Test.’’ UAL also 

asked that the procedure specified in 

AMM Task 28–22–07–706–200, titled 

‘‘Engine Fuel Feed Manifold Air 

Pressure Leak Check,’’ be included as an 

alternative procedure. 

We do not agree with the commenter’s 

request, but provide the following 

clarification. The manifold leak test is 

not equivalent to the operational test for 

the purposes of this AD action. The 

positive internal fuel line pressure 

applied during the manifold test does 

not simulate the same conditions 

encountered during fuel suction feed 

(i.e., vacuum), and might mask a failure. 

The action mandated by this AD is 

necessary in order to screen for system 

deterioration under suction feed 

conditions. Based on current 

requirements, a fuel suction feed test is 

required after reconnecting the fuel line 

to the manifold to verify final system 

integrity. Therefore, we have not 

changed the AD in this regard. 

Request for Additional Step in 

Operational Test 

UPS asked that we add a tolerance to 

the operational test for Steps 10.a and 

10.c for the N1, N2, and ‘‘Fuel Flow 

Decrease Monitoring.’’ (UPS stated that 

this follows the procedures in the 

referenced service information.) UPS is 

concerned that the engine parameters 

monitored using Step 10 might have 

slight (normal) fluctuations due to 

external effects, such as wind gusts, 

which could lead to a false test failure. 

We do not agree with the commenter’s 

request. These defined criteria were 

taken directly from approved AMMs 

that describe similar testing. These 

criteria have been used for a very long 

time with no negative feedback or 

requests for a similar (wider) tolerance 

band. In light of these facts, we have 

made no change to the AD in this 

regard. 

Request to Provide Credit for 

Previously Accomplished Operational 

Tests 

UAL asked that the SNPRM (77 FR 

40307, July 9, 2012) be changed to 

provide credit for operational tests of 

the engine fuel suction system 

previously accomplished as specified in 

MRB Task 28–022–04, titled 

‘‘Operational Check of the Engine Fuel 

Suction Feed System.’’ UAL stated that 

it has incorporated this MRB task into 

its maintenance program at the MRB 

recommended level. UAL inferred that 

other operators of Model 747–400 

airplanes have done the same. 

We agree that credit might be 

appropriate for operator equivalent 

procedures; however, we do not agree 

with defining this credit within the AD. 


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Federal Register / Vol. 78, No. 127 / Tuesday, July 2, 2013 / Rules and Regulations 39573 

Affected operators may request approval 

of an AMOC under the provisions of 

paragraph (h) of this AD by submitting 

data substantiating that the equivalent 

procedures would provide an acceptable 

level of safety. We have not changed the 

AD in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously– 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM (77 FR 

40307, July 9, 2012) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (77 FR 40307, 

July 9, 2012). 

We also determined that this change 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

We estimate that this AD affects 79 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Cost per 

product 

Cost on U.S. 

operators 

Operational Test ...................................... 3 work-hours × $85 per hour = $255 per 

engine, per test.

$1,020, per test ................... $80,580, per test. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this 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. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will 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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 airworthiness 

directive (AD): 

2013–13–11 The Boeing Company: 

Amendment 39–17499; Docket No. 

FAA–2008–0620; Directorate Identifier 

2007–NM–357–AD. 

(a) Effective Date 

This AD is effective August 6, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–400, -400D, and -400F series 

airplanes, certificated in any category, as 

identified in Boeing Alert Service Bulletin 

747–28A2330, dated April 2, 2012. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 2800, Aircraft Fuel System. 

(e) Unsafe Condition 

This AD was prompted by reports of two 

in-service occurrences on Model 737–400 

airplanes of total loss of boost pump pressure 

of the fuel feed system, followed by loss of 

fuel system suction feed capability on one 

engine, and in-flight shutdown of the engine. 

We are issuing this AD to detect and correct 

loss of the engine fuel suction feed capability 

of the fuel system, which, in the event of 

total loss of the fuel boost pumps, could 

result in multi-engine flameout, inability to 

restart the engines, and consequent forced 

landing of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Operational Test and Corrective Actions 

Within 30,000 flight hours after the 

effective date of this AD: Perform an 

operational test of the engine fuel suction 

feed of the fuel system, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–28A2330, dated April 2, 

2012; or Boeing Service Bulletin 747– 

28A2330, Revision 1, dated November 30, 

2012. Do all applicable corrective actions 

before further flight. Repeat the operational 

test thereafter at intervals not to exceed 

30,000 flight hours. Thereafter, except as 

provided in paragraph (h) of this AD, no 

alternative procedures or repetitive test 

intervals will be allowed. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 


emcdonald on DSK67QTVN1PROD with RULES
39574 Federal Register / Vol. 78, No. 127 / Tuesday, July 2, 2013 / Rules and Regulations 

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. 

(i) Related Information 

For more information about this AD, 

contact Sue Lucier, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6438; fax: 425–917– 

6590; email: suzanne.lucier@faa.gov. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 747– 

28A2330, dated April 2, 2012. 

(ii) Boeing Service Bulletin 747–28A2330, 

Revision 1, dated November 30, 2012. 

(3) 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. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, June 13, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–15692 Filed 7–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0214; Directorate 

Identifier 2012–NM–152–AD; Amendment 

39–17497; AD 2013–13–09] 

RIN 2120–AA64 

Airworthiness Directives; Learjet Inc. 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Learjet Inc. Model 60 airplanes. This AD 

was prompted by a report of a highspeed rejected takeoff caused by all four 

main landing gear (MLG) tires blowing 

out during the takeoff roll. This AD 

requires installing new rigid hydraulic 

tube assemblies to the MLG struts; 

installing a new MLG squat switch 

bracket, modifying the MLG squat 

switch wire harness; modifying the 

MLG anti-skid wheel transducer 

electrical wire harnesses; routing and 

securing the anti-skid wheel and squat 

switch electrical wire harnesses to the 

MLG strut assembly; installing outboard 

bracket assemblies, anti-skid shield, 

forward electrical cover on the forward 

stiffener, upper and lower inboard 

bracket assemblies, and clamps that 

support the electrical wire harness; 

modifying the aft stiffener for the new 

electrical wire harness support; 

installing the aft electrical cover and 

strap on the aft stiffener; installing a 

new flat landing light lamp if necessary; 

and, for certain airplanes, installing a 

new wheel speed detect box assembly, 

nutplates, and brackets and a new thrust 

reverser interface box, and modifying 

the wiring for the new thrust reverser 

interface box. We are issuing this AD to 

prevent failure of the braking system or 

adverse operation of the spoiler and 

thrust reverser system due to external 

damage, particularly from tire failure, 

which could result in loss of control of 

the airplane. 

DATES: This AD is effective August 6, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of August 6, 2013. 

ADDRESSES: 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Don 

Ristow, Aerospace Engineer, 

Mechanical Systems and Propulsion 

Branch, ACE–116W, FAA, Wichita 

Aircraft Certification Office, 1801 

Airport Road, Room 100, Mid-Continent 

Airport, Wichita, KS 67209; phone: 

316–946–4120; fax: 316–946–4107; 

email: donald.ristow@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on March 27, 2013 (78 FR 

18531). The NPRM proposed to require 

installing new rigid hydraulic tube 

assemblies to the MLG struts; installing 

a new MLG squat switch bracket; 

modifying the MLG squat switch wire 

harness; modifying the MLG anti-skid 

wheel transducer electrical wire 

harnesses; routing and securing the antiskid wheel and squat switch electrical 

wire harnesses to the MLG strut 

assembly; installing outboard bracket 

assemblies, anti-skid shield, forward 

electrical cover on the forward stiffener, 

upper and lower inboard bracket 

assemblies, and clamps that support the 

electrical wire harness; modifying the 

aft stiffener for the new electrical wire 

harness support; installing the aft 

electrical cover and strap on the aft 

stiffener; installing a new flat landing 

light lamp if necessary; and, for certain 

airplanes, installing a new wheel speed 

detect box assembly, nutplates, and 

brackets and a new thrust reverser 


emcdonald on DSK67QTVN1PROD with RULES