Federal Register / Vol. 79, No. 27 / Monday, February 10, 2014 / Proposed Rules 7601 

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 (l)(1) 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. 

(l) Related Information 

(1) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6577; fax: 425–917–6590; 

email: Berhane.Alazar@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

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

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

may view this service information at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

Issued in Renton, Washington, on January 

18, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–02717 Filed 2–7–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0010; Directorate 

Identifier 2012–NM–218–AD] 

RIN 2120–AA64 

Airworthiness Directives; Learjet Inc. 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Learjet Inc. Model 45 airplanes. This 

proposed AD was prompted by a report 

of two cases of premature corrosion 

found on the structural support flange 

for the engine thrust reverser. This 

proposed AD would 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 

proposing 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: We must receive comments on 

this proposed AD by March 27, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact 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 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, 

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: 

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– 

2014–0010; Directorate Identifier 2012– 

NM–218–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 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. This 

condition, if not corrected, could result 

in 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. 

Relevant Service Information 

We reviewed Bombardier Service 

Bulletin 40–78–03, Revision 1, dated 


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7602 Federal Register / Vol. 79, No. 27 / Monday, February 10, 2014 / Proposed Rules 

November 5, 2012 (for Model 45 

airplanes having S/N 45–2001 through 

45–2132); and Bombardier Service 

Bulletin 45–78–9, Revision 1, dated 

November 5, 2012 (for Model 45 

airplanes having S/N 45–005 through 

45–436). Those service bulletins 

describe inspecting the thrust reverser’s 

attach flange for damage to the sealant, 

as applicable, and installing sealants 

and gaskets as applicable to the thrust 

reverser flanges and service island 

flanges. 

We also reviewed Nordam Service 

Bulletin 5045 78–13, dated January 17, 

2012 (for Model 45 airplanes having 

S/N 45–005 through 45–420 inclusive 

and S/N 45–2001 through 45–2129 

inclusive), which describes procedures 

for fluorescent penetrant inspection of 

the metallic components of the thrust 

reverser’s attach flange for any 

corrosion, and related investigative and 

corrective actions. Corrective actions 

include removing corrosion from the 

thrust reverser’s attach flange, applying 

finishes, contacting the manufacturer, 

and replacing the engine attach flange. 

Related investigative actions include 

doing further fluorescent penetrant 

inspection for any remaining corrosion, 

and measuring to ensure a minimum 

material thickness. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Difference Between the Proposed AD 

and the Service Information.’’ 

Difference Between Proposed AD and 

the Service Information 

Although Nordam Service Bulletin 

5045 78–13, dated January 17, 2012, 

specifies that operators may contact the 

manufacturer for disposition of certain 

repair conditions, this proposed AD 

would require operators to repair those 

conditions in accordance with a method 

approved by the FAA. 

Costs of Compliance 

We estimate that this proposed AD 

affects 365 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 Number of 

U.S. products 

Cost on U.S. operators 

Inspections and installing sealants 

and gaskets.

Between 26 and 36 workhours × $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 

proposed 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 proposed 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 

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: 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 27 / Monday, February 10, 2014 / Proposed Rules 7603 

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–2014–0010; 

Directorate Identifier 2012–NM–218–AD. 

(a) Comments Due Date 

We must receive comments by March 27, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Learjet Inc. Model 45 

airplanes having serial numbers (S/N) 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 Lear 40 Model 45 

airplanes as a marketing designation. 

(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. 

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/N 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/N 45–005 

through 45–436 inclusive). 

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

2001 through 45–2129 inclusive and S/N 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/N 45–2001 through 45–2132); or 

Bombardier Service Bulletin 45–78–9, dated 

February 27, 2012 (for Model 45 airplanes 

having S/N 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) 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, Washington. For 

information on the availability of this 

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

Issued in Renton, Washington, on January 

22, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–02715 Filed 2–7–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0807; Directorate 

Identifier 2011–NM–191–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for all Airbus Model A318 series 

airplanes, and Model A319, A320, and 

A321 series airplanes. The NPRM 

proposed identifying the part number 

and serial number of each passenger 

oxygen container, replacing the oxygen 

generator manifold of the affected 

oxygen container with a serviceable 

manifold, and performing an 

operational check of the manual mask 

release, and corrective actions if 

necessary. The NPRM was prompted by 

reports of silicon particles inside the 

oxygen generator manifolds, which had 

chafed from the mask hoses during 

installation onto the generator outlets. 

This action revises the NPRM by adding 

airplanes to the applicability, adding a 

new check for part numbers, corrective 

actions if necessary, and reducing the 

compliance time for certain actions. We 

are proposing this AD to detect and 

correct non-serviceable oxygen 

generator manifolds, which could 

reduce or block the oxygen supply and 

result in injury to passengers when 

oxygen supply is needed. Since these 


emcdonald on DSK67QTVN1PROD with PROPOSALS