Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 41087 

Departing thrust reversers could also result in 

injury to persons on the ground. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections and Sealant Installation With 

Applicable Related Investigative and 

Corrective Actions 

Within 1,200 flight hours or 48 months 

after the effective date of this AD, whichever 

occurs first, do the requirements of paragraph 

(g)(1) of this AD; and for the airplanes 

identified in paragraph (g)(2) of this AD, do 

the requirements of paragraph (g)(2) of this 

AD concurrently. 

(1) Do a detailed inspection of the thrust 

reverser flange for damage to the sealant, as 

applicable, and install sealants and gaskets 

before further flight, as applicable, to the 

thrust reverser flanges and service island 

flanges, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 40–78–03, Revision 1, dated 

November 5, 2012 (for Model 45 airplanes 

having S/Ns 45–2001 through 45–2132 

inclusive); or Bombardier Service Bulletin 

45–78–9, Revision 1, dated November 5, 2012 

(for Model 45 airplanes having S/Ns 45–005 

through 45–436 inclusive). 

(2) For Model 45 airplanes having S/Ns 45– 

2001 through 45–2129 inclusive and S/Ns 

45–005 through 45–420 inclusive: Do a 

fluorescent penetrant inspection for 

corrosion of the metallic components of the 

thrust reverser’s attach flange for any 

corrosion, and all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Nordam Service Bulletin 5045 

78–13, dated January 17, 2012, except as 

required by paragraph (h) of this AD. Do all 

applicable related investigative and 

corrective actions before further flight. 

(h) Exception to the Nordam Service 

Information 

If any material thickness less than the 

minimum allowable thickness is found 

during any inspection required by paragraph 

(g)(2) of this AD, and Nordam Service 

Bulletin 5045 78–13, dated January 17, 2012, 

specifies contacting Bombardier Learjet for 

appropriate action: Before further flight, 

repair the thrust reverser’s attach flange in 

accordance with a method approved by the 

Manager, Wichita Aircraft Certification Office 

(ACO), FAA. For a repair method to be 

approved by the Manager, Wichita ACO, as 

required by this paragraph, the Manager’s 

approval letter must specifically refer to this 

AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Bombardier 

Service Bulletin 40–78–03, dated February 

27, 2012 (for Model 45 airplanes having S/ 

Ns 45–2001 through 45–2132); or Bombardier 

Service Bulletin 45–78–9, dated February 27, 

2012 (for Model 45 airplanes having S/Ns 

45–005 through 45–436). 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita 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 

paragraph (k)(1) 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. 

(k) Related Information 

(1) For more information about this AD, 

contact Paul Chapman, Aerospace Engineer, 

Airframe and Services Branch, 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; email: 

paul.chapman@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

paragraphs (l)(3) and (l)(4) of this AD. 

(l) 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. 

(i) Bombardier Service Bulletin 40–78–03, 

Revision 1, dated November 5, 2012. 

(ii) Bombardier Service Bulletin 45–78–9, 

Revision 1, dated November 5, 2012. 

(iii) Nordam Service Bulletin 5045 78–13, 

dated January 17, 2012. 

(3) For Learjet and Nordam 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. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA 98057–3356. 

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, on June 19, 

2014. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–15377 Filed 7–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0863; Directorate 

Identifier 2012–NM–108–AD; Amendment 

39–17883; AD 2014–13–07] 

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 737–300, 

–400, –500, –600, –700, –700C, –800, 

–900, and –900ER series airplanes. This 

AD was prompted by a review of the tail 

strobe light installation, which revealed 

that the tail strobe light is not 

electrically bonded to primary structure 

of the airplane. This AD requires 

installing a new tail strobe light housing 

and a new disconnect bracket, and 

changing the wire bundles. This AD also 

requires, for certain airplanes, an 

inspection to determine if sealant is 

applied, and corrective actions if 

necessary. We are issuing this AD to 

prevent, in case of a direct lightning 

strike to the tail strobe light, damage to 

the operation of other critical airplane 

systems due to electromagnetic coupling 

and large transient voltages, and damage 

to the control mechanisms or surfaces 

due to a fire, which could result in loss 

of control of the airplane. 

DATES: This AD is effective August 19, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 19, 2014. 

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 view 

this 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 by searching for 

and locating Docket No. FAA–2012– 


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41088 Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 

0863; 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 

Docket 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: 

Marie Hogestad, Aerospace Engineer, 

Systems and Equipment Branch, FAA, 

ANM–130S, Seattle Aircraft 

Certification Office, 1601 Lind Avenue 

SW., Renton, WA 98057–3356; phone: 

425–917–6418; fax: 425–917–6590; 

email: marie.hogestad@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 by adding an AD 

that would apply to certain The Boeing 

Company Model 737–300, –400, –500, 

–600, –700, –700C, –800, –900, and 

–900ER series airplanes. The SNPRM 

published in the Federal Register on 

March 12, 2014 (79 FR 13934). We 

preceded the SNPRM with a notice of 

proposed rulemaking (NPRM) that 

published in the Federal Register on 

September 6, 2012 (77 FR 54848). The 

NPRM proposed to require installing a 

new tail strobe light housing and a new 

disconnect bracket, and changing the 

wire bundles. The NPRM was prompted 

by a review of the tail strobe light 

installation, which revealed that the tail 

strobe light is not electrically bonded to 

primary structure of the airplane. The 

SNPRM proposed to add, for certain 

airplanes, an inspection to determine if 

sealant is applied and corrective actions 

if necessary. We are issuing this AD to 

prevent, in case of a direct lightning 

strike to the tail strobe light, damage to 

the operation of other critical airplane 

systems due to electromagnetic coupling 

and large transient voltages, and damage 

to the control mechanisms or surfaces 

due to a fire, which could result in loss 

of control of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM 

(79 FR 13934, March 12, 2014) or on the 

determination of the cost to the public. 

Clarification 

We have changed the paragraph 

heading for paragraph (h) of this AD to 

more accurately reflect the required 

actions therein. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM (79 FR 

13934, March 12, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (79 FR 13934, 

March 12, 2014). 

Costs of Compliance 

We estimate that this AD affects 1,433 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Installation for Model 737–300, –400, and 

–500 series airplanes, as identified in Boeing Special Attention Service Bulletin 737– 

33–1149, dated April 13, 2012 (396 U.S. 

registered airplanes).

Up to 32 work-hours × $85 per 

hour = Up to $2,720.

Up to $14,886 ........... Up to $17,606 Up to $6,971,976. 

Installation for Model 737–600, –700, –700C, 

–800, –900, and –900ER series airplanes, 

Group 1, as identified in Boeing Special 

Attention Service Bulletin 737–33–1146, 

Revision 1, dated July 9, 2013 (465 U.S. 

registered airplanes).

Up to 21 work-hours × $85 per 

hour = Up to $1,785.

Up to $4,422 ............. Up to $6,207 ... Up to $2,886,255. 

Installation for Model 737–600, –700, –700C, 

–800, –900, and –900ER series airplanes, 

Group 2, as identified in Boeing Special 

Attention Service Bulletin 737–33–1146, 

Revision 1, dated July 9, 2013 (83 U.S. 

registered airplanes).

Up to 21 work-hours × $85 per 

hour = Up to $1,785.

Up to $2,496 ............. Up to $4,281 ... Up to $355,323. 

Installation for Model 737–600, –700, –700C, 

–800, –900, and –900ER series airplanes, 

Group 3, as identified in Boeing Special 

Attention Service Bulletin 737–33–1146, 

Revision 1, dated July 9, 2013 (25 U.S. 

registered airplanes).

Up to 20 work-hours × $85 per 

hour = Up to $1,700.

Up to $4,478 ............. Up to $6,178 ... Up to $154,450. 

Installation for Model 737–600, –700, –700C, 

–800, –900, and –900ER series airplanes, 

Group 4, as identified in Boeing Special 

Attention Service Bulletin 737–33–1146, 

Revision 1, dated July 9, 2013 (464 U.S. 

registered airplanes).

Up to 21 work-hours × $85 per 

hour = Up to $1,785.

Up to $4,423 ............. Up to $6,208 ... Up to $2,880,512. 


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Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 41089 

ESTIMATED COSTS—Continued 

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection for Model 737–600, –700, –700C, 

–800, –900 and –900ER series airplanes, 

as identified in Boeing Special Attention 

Service Bulletin 737–33–1146, Revision 1, 

dated July 9, 2013 (up to 1,037 U.S. registered airplanes).

Up to 2 work-hours × $85 per 

hour = Up to $170.

$0 .............................. Up to $170 ...... Up to $176,290. 

We estimate the following cost to 

apply sealant, based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need this sealant application: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Sealant application ........................... 1 work-hour × $85 per hour = $85 ............................................................. Negligible .... $85 

The parts cost to apply sealant 

between the disconnect bracket and the 

receptacle connector D44582J, and on 

the fasteners is not included in the 

estimate. It is considered ‘‘Parts & 

Materials Supplied by the Operator,’’ 

which is referenced in Boeing Special 

Attention Service Bulletin 737–33– 

1146, Revision 1, dated July 9, 2013. 

According to the manufacturer, all of 

the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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): 

2014–13–07 The Boeing Company: 

Amendment 39–17883; Docket No. 

FAA–2012–0863; Directorate Identifier 

2012–NM–108–AD. 

(a) Effective Date 

This AD is effective August 19, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

airplanes, certificated in any category, as 

identified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) Model 737–300, –400, and –500 series 

airplanes, as identified in Boeing Special 

Attention Service Bulletin 737–33–1149, 

dated April 13, 2012. 

(2) Model 737–600, –700, –700C, –800, 

–900, and –900ER series airplanes, as 

identified in Boeing Special Attention 

Service Bulletin 737–33–1146, Revision 1, 

dated July 9, 2013. 

(3) Installation of Supplemental Type 

Certificate (STC) ST00830SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

da95c49000906c7086257be80044d3d9/

$FILE/ST00830SE.pdf) does not affect the 

ability to accomplish the actions required by 

this AD. Therefore, for airplanes on which 

STC ST00830SE is installed, a ‘‘change in 

product’’ alternative method of compliance 

(AMOC) approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 33, Lights. 


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(e) Unsafe Condition 

This AD was prompted by a review of the 

tail strobe light installation, which revealed 

that the tail strobe light is not electrically 

bonded to primary structure of the airplane. 

We are issuing this AD to prevent, in case of 

a direct lightning strike to the tail strobe 

light, damage to the operation of other 

critical airplane systems due to 

electromagnetic coupling and large transient 

voltages, and damage to the control 

mechanisms or surfaces due to a fire, which 

could result in loss of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Tail Strobe Light Installation for Model 

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

–900ER Series Airplanes 

For Model 737–600, –700, –700C, –800, 

–900, and –900ER series airplanes on which 

the actions specified in Boeing Special 

Attention Service Bulletin 737–33–1146, 

dated November 2, 2011, have not been done 

before the effective date of this AD: Within 

72 months after the effective date of this AD, 

install a new tail strobe light housing, install 

a new disconnect bracket, and change the 

wire bundles, in accordance with Part 1 of 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–33– 

1146, Revision 1, dated July 9, 2013, except 

as required by paragraphs (g)(1) and (g)(2) of 

this AD. 

(1) Where Figure 8, Flag Note 3, of Boeing 

Special Attention Service Bulletin 737–33– 

1146, Revision 1, dated July 9, 2013, refers 

to solder sleeve BACS13CT3C, the shield 

splice contained in splice kit D–150–0168 

may be used in lieu of solder sleeve 

(BACS13CT3C), provided a ground wire is 

used. 

Note 1 to paragraph (g)(1) of this AD: 

Guidance for wire-type information for the 

ground wires may be found in Boeing 

Standard Wiring Practices Manual (SWPM) 

D6–54446, Section 20–10–15. 

(2) Where the second sentence of note (c) 

of Figure 3 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–33–1146, Revision 1, 

dated July 9, 2013, specifies to ‘‘Maintain a 

minimum of 1.7 Dimensions fastener edge 

margin on the disconnect bracket and the 

stiffener,’’ instead ‘‘Maintain a minimum of 

1.7 diameter fastener edge margin on the 

disconnect bracket and the stiffener.’’ 

(h) Inspection and Corrective Actions for 

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

–900ER Series Airplanes 

For Model 737–600, –700, –700C, –800, 

–900, and –900ER series airplanes, on which 

the actions specified in Boeing Special 

Attention Service Bulletin 737–33–1146, 

dated November 2, 2011, have been done 

before the effective date of this AD: Within 

72 months after the effective date of this AD, 

do a general visual inspection to ensure there 

is fillet sealant between the disconnect 

bracket and the receptacle connector 

D44582J, and on the fasteners, and do all 

applicable corrective actions, in accordance 

with Part 2 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–33–1146, Revision 1, 

dated July 9, 2013. Do all applicable 

corrective actions before further flight. 

(i) Tail Strobe Light Installation for Model 

737–300, –400, and –500 Series Airplanes 

For Model 737–300, –400, and –500 series 

airplanes: Within 72 months after the 

effective date of this AD, install a new tail 

strobe light housing, install a new disconnect 

bracket, and change the wire bundles, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–33–1149, dated April 

13, 2012. 

(j) 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 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (k) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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 Organization 

Designation Authorization (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. 

(k) Related Information 

(1) For more information about this AD, 

contact Marie Hogestad, Aerospace Engineer, 

Systems and Equipment Branch, FAA, ANM– 

130S, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6418; fax: 425–917– 

6590; email: marie.hogestad@faa.gov. 

(2) For service information identified in 

this AD that is not incorporated by reference 

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 view this 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. 

(l) 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. 

(i) Boeing Special Attention Service 

Bulletin 737–33–1146, Revision 1, dated July 

9, 2013. 

(ii) Boeing Special Attention Service 

Bulletin 737–33–1149, dated April 13, 2012. 

(3) For Boeing 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 view this service information 

at 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. 

(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, on June 19, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–15382 Filed 7–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1027; Directorate 

Identifier 2013–NM–121–AD; Amendment 

39–17886; AD 2014–13–10] 

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 737–600, 

–700, –700C, –800, –900, and –900ER 

series airplanes. This AD was prompted 

by a report of installation of incorrect 

wire support clamps within the bay area 

of the left and right environmental 

control systems (ECS) during 

production; the ECS bay area is a 

flammable fluid leakage zone. Use of 

incorrect wire support clamps that are 

not fully cushioned could allow 

electrical power wiring to come in 

contact with the exposed metal of the 

improper clamp, causing a short circuit 


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