This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

41085 

Vol. 79, No. 135 

Tuesday, July 15, 2014 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0010; Directorate 

Identifier 2012–NM–218–AD; Amendment 

39–17882; AD 2014–13–06] 

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 45 airplanes. This AD 

was prompted by a report of two cases 

of premature corrosion found on the 

structural support flange for the engine 

thrust reverser. This AD requires 

inspecting for any corrosion, and 

damage to the sealant; installing 

sealants and gaskets; and related 

investigative and corrective actions as 

necessary. We are issuing this AD to 

prevent failure of the thrust reverser 

structural support, which could result 

in departure of the thrust reverser from 

the engine that could subsequently 

result in damage to the adjacent support 

structure and engine controls, airframe 

structure, and control surfaces. 

Departing thrust reversers could also 

result in injury to persons on the 

ground. 

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 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 view 

this referenced service information at 

the 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. 

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–2014– 

0010; 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: 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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Learjet Inc. Model 45 

airplanes. The NPRM published in the 

Federal Register on February 10, 2014 

(79 FR 7601). The NPRM was prompted 

by a report of two cases of premature 

corrosion found on the structural 

support flange for the engine thrust 

reverser that attaches the thrust reverser 

to the engine. The thrust reverser’s 

attach flange is made of aluminum and 

the corrosion of that flange can be 

caused by contact with exposed graphite 

fibers from the engine’s composite 

bypass duct. The NPRM proposed to 

require doing a fluorescent penetrant 

inspection of the metallic components 

of the thrust reverser’s attach flange for 

any corrosion; inspecting the thrust 

reverser flange for damage to the 

sealant, as applicable; installing sealants 

and gaskets, as applicable, to the thrust 

reverser flanges and service island 

flanges; and related investigative and 

corrective actions as necessary. We are 

issuing this AD to prevent failure of the 

thrust reverser structural support, which 

could result in departure of the thrust 

reverser from the engine that could 

subsequently result in damage to the 

adjacent support structure and engine 

controls, airframe structure, and control 

surfaces. Departing thrust reversers 

could also result in injury to persons on 

the ground. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Request To Add Service Information to 

Paragraph (i) of This AD 

Bombardier requested that paragraph 

(i) of the proposed AD (79 FR 1601, 

February 10, 2014) be revised to add 

Bombardier Service Bulletin 40–78–03, 

Revision 1, dated November 5, 2012; or 

Bombardier Service Bulletin 45–78–9, 

Revision 1, dated November 5, 2012. 

Bombardier stated that adding this 

service information to paragraph (i) of 

the proposed AD would allow credit for 

accomplishing the requirements of 

paragraph (g) of the proposed AD before 

the effective date of the AD. 

We disagree with revising paragraph 

(i) of this AD. The purpose of paragraph 

(i) of this AD is to allow credit for using 

an earlier revision of the required 

service information before the effective 

date of the AD if that earlier revision is 

considered acceptable for addressing the 

unsafe condition. If actions required by 

paragraph (g) of this AD were 

accomplished before the effective date 

of the AD, using the service information 

required by paragraph (g) of this AD, 

those actions are considered acceptable 

for compliance, since paragraph (f) of 

this AD states ‘‘Comply with this AD 

within the compliance times specified, 

unless already done.’’ We have not 

changed this AD in this regard. 

Clarification of Marketing Designation 

We have revised Note 1 to paragraph 

(c) of this AD to clarify the marketing 

designations that Model 45 airplanes 

might be known as. 


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41086 Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 

Conclusion 

We reviewed the relevant data, 

considered the comment received, 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 NPRM (79 FR 1601, 

February 10, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 1601, 

February 10, 2014). 

Costs of Compliance 

We estimate that this AD affects 365 

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 Number of U.S. 

products 

Cost on U.S. 

operators 

Inspections and installing sealants 

and gaskets.

Between 26 and 36 work-hours × $85 

per hour = Between $2,210 and 

$3,060 per thrust reverser.

Between $1,216 

and $1,476 per 

thrust reverser.

Between $3,426 

and $4,536 per 

thrust reverser.

730 thrust reversers (365 airplanes).Between 

$2,500,980 and 

$3,311,280. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need this replacement. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Replacing thrust reverser 

attachment flange.

40 work-hours × $85 per hour = $3,400 per thrust reverser.$1,200 per thrust reverser $4,600 per thrust reverser. 

According to the manufacturer, some 

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): 

2014–13–06 Learjet Inc.: Amendment 39– 

17882; Docket No. FAA–2014–0010; 

Directorate Identifier 2012–NM–218–AD. 

(a) Effective Date 

This AD is effective August 19, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Learjet Inc. Model 45 

airplanes having serial numbers (S/Ns) 45– 

005 through 45–436 inclusive, and 45–2001 

through 45–2132 inclusive, certificated in 

any category, that are equipped with 

composite engine fan bypass ducts. 

Note 1 to paragraph (c) of this AD: Learjet 

Model 45 airplanes having S/Ns 45–2001 and 

subsequent are commonly referred to as 

‘‘Model 40’’ airplanes or Learjet 40 airplanes 

as marketing designations. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 78, Engine Exhaust. 

(e) Unsafe Condition 

This AD was prompted by a report of two 

cases of premature corrosion found on the 

structural support flange for the engine thrust 

reverser. We are issuing this AD to prevent 

failure of the thrust reverser structural 

support, which could result in departure of 

the thrust reverser from the engine that could 

subsequently result in damage to the adjacent 

support structure and engine controls, 

airframe structure, and control surfaces. 


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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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