7598 Federal Register / Vol. 79, No. 27 / Monday, February 10, 2014 / Proposed Rules 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Airbus: Docket No. FAA–2014–0004; 

Directorate Identifier 2013–NM–143–AD. 

(a) Comments Due Date 

We must receive comments by March 27, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A320– 

211, –212, and –231 airplanes, certificated in 

any category, all manufacturer serial numbers 

up to 0136 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports of 

broken struts of the center wing box (CWB) 

on certain airplanes. We are issuing this AD 

to detect and correct cracked or broken struts, 

which could result in struts, which could 

result in strut failure and consequent reduced 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

At the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD: Do a 

detailed inspection of each strut of the CWB 

for cracking, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1149, Revision 01, 

dated February 12, 2013. Repeat the 

inspection thereafter at intervals not to 

exceed 16,800 flight cycles or 33,600 flight 

hours, whichever occurs first. 

(1) For airplanes on which the inspection 

required by paragraph (g) of this AD has not 

been done as of the effective date of this AD: 

Do the inspection at the later of the times 

specified in paragraphs (g)(1)(i) and (g)(1)(ii) 

of this AD. 

(i) Before the accumulation of 31,700 total 

flight cycles or 63,400 total flight hours since 

first flight, whichever occurs first. 

(ii) Within 1,250 flight cycles or 2,500 

flight hours after the effective date of this AD, 

whichever occurs first. 

(2) For airplanes on which the inspection 

required by paragraph (g) of this AD has been 

done as of the effective date of this AD: Do 

the inspection within 16,800 flight cycles or 

33,600 flight hours after the most recent 

inspection, whichever occurs first. 

(h) Repair 

If any crack is found during any inspection 

required by paragraph (g) of this AD: Before 

further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; the EASA (or its delegated 

agent, or the Design Approval Holder with 

EASA’s design organization approval). For a 

repair method to be approved, the repair 

approval must specifically refer to this AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Airbus Service Bulletin 

A320–57–1149, dated April 1, 2008. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–227–1405; 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, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the DAH with a State 

of Design Authority’s design organization 

approval). You are required to ensure the 

product is airworthy before it is returned to 

service. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0149, dated 

July 16, 2013, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating it in Docket No. 

FAA–2014–0004. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.com. 

(3) You may view copies of 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. 2014–02718 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–2014–0009; Directorate 

Identifier 2013–NM–123–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all The 

Boeing Company Model 707 airplanes, 

and Model 720 and 720B series 

airplanes. This proposed AD was 

prompted by reports of scribe-linerelated fatigue cracks on Model 727 

airplanes, which are similar in design to 

Model 707 airplanes, and Model 720 

and 720B series airplanes. This 

proposed AD would require inspections 

for scribe lines in the skin lap joints, 

external approved repairs, external 

features, skin butt joints, and decals, 

and related investigative and corrective 

actions if necessary. This proposed AD 

would also require surface finish 

restoration. We are proposing this AD to 

detect and correct scribe lines, which 

can develop into fatigue cracks in the 

skin and cause rapid decompression of 

the airplane. 

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 


emcdonald on DSK67QTVN1PROD with PROPOSALS
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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 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. 

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– 

0009; 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: 

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. 

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– 

2014–0009; Directorate Identifier 2013– 

NM–123–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 have received reports of scribeline-related fatigue cracks on two Model 

727 airplanes, which are similar in 

design to Model 707 airplanes, and 

Model 720 and 720B series airplanes. 

One report was on a Model 727–100 

airplane with 44,171 total flight cycles. 

The crack was near a repaired area and 

caused rapid decompression of the 

airplane. Another report was on a Model 

727–100 airplane with 51,195 total 

flight cycles. The crack was at station 

1090–1110, at the stringer 4L lap joint. 

This also resulted in rapid 

decompression of the airplane. Scribe 

lines could result in fatigue cracks 

developing in the skin at scribe line 

locations. Fatigue cracks, if not 

corrected, could grow large and cause 

rapid decompression of the airplane. 

Related ADs 

This proposed AD is similar to the 

following four ADs, which require 

inspections to detect scribe lines in the 

fuselage skin at certain lap joints, 

around decal locations, external repair 

doublers, and other areas, and related 

investigative and corrective actions if 

necessary. Those ADs resulted from 

reports of fuselage skin cracks adjacent 

to the skin lap joints on airplanes that 

had scribe lines. 

• AD 2013–07–11, Amendment 39– 

17415 (78 FR 22185, April 15, 2013), for 

certain Boeing Model 777–200, –200LR, 

–300, and –300ER series airplanes. 

• AD 2010–06–16, Amendment 39– 

16241 (75 FR 12670, March 17, 2010), 

for certain Boeing Model 767 series 

airplanes. 

• AD 2010–05–13, Amendment 39– 

16223 (75 FR 10658, March 9, 2010), 

corrected March 19, 2010 (75 FR 13225) 

for all Boeing Model 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. 

• AD 2007–19–07, Amendment 39– 

15198 (72 FR 60244, October 24, 2007), 

for certain Boeing Model 757–200, 

–200PF, and –200CB series airplanes. 

Relevant Service Information 

We reviewed Boeing 707 Alert Service 

Bulletin A3539, dated April 26, 2013. 

For information on the procedures and 

compliance times, see this service 

information at http://

www.regulations.gov by searching for 

Docket No. FAA–2014–0009. 

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 identified 

previously, except as discussed under 

‘‘Differences Between the Proposed AD 

and the Service Information.’’ 

The phrase ‘‘related investigative 

actions’’ is used in this proposed AD. 

‘‘Related investigative actions’’ are 

follow-on actions that: (1) Are related to 

the primary actions, and (2) further 

investigate the nature of any condition 

found. Related investigative actions in 

an AD could include, for example, 

inspections. 

In addition, the phrase ‘‘corrective 

actions’’ is used in this proposed AD. 

‘‘Corrective actions’’ are actions that 

correct or address any condition found. 

Corrective actions in an AD could 

include, for example, repairs. 

Differences Between the Proposed AD 

and the Service Information 

Boeing 707 Alert Service Bulletin 

A3539, dated April 26, 2013, specifies 

to contact the manufacturer for 

instructions on how to accomplish 

repairs, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

affects 11 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


emcdonald on DSK67QTVN1PROD with PROPOSALS
7600 Federal Register / Vol. 79, No. 27 / Monday, February 10, 2014 / Proposed Rules 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection ........................................................ 96 work-hours × $85 per hour = $8,160 ........ $0 $8,160 $89,760 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed 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 

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: 

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): 

The Boeing Company: Docket No. FAA– 

2014–0009; Directorate Identifier 2013– 

NM–123–AD. 

(a) Comments Due Date 

We must receive comments by March 27, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

airplanes, certificated in any category, 

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

this AD. 

(1) All Model 707–100 long body, –200, 

–100B long body, and –100B short body 

series airplanes; and Model 707–300, –300B, 

–300C, and –400 series airplanes. 

(2) All Model 720 and 720B series 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

scribe-line-related fatigue cracks on Model 

727 airplanes, which are similar in design to 

the Model 707 airplanes, and Model 720 and 

720B series airplanes. We are issuing this AD 

to detect and correct scribe lines, which can 

develop into fatigue cracks in the skin and 

cause rapid decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Scribe Line Inspection 

(1) Except as specified in paragraphs (j)(1) 

and (j)(2) of this AD, at the applicable time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing 707 Alert Service Bulletin A3539, 

dated April 26, 2013: Do a detailed 

inspection of the fuselage skin for scribe 

lines, in accordance with the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3539, dated April 26, 

2013. If no scribe line is found: Before further 

flight, do surface finish restoration, in 

accordance with the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3539, dated April 26, 2013. 

(2) The inspection exceptions described in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 

Alert Service Bulletin A3539, dated April 26, 

2013, apply to paragraph (g)(1) of this AD. 

(h) Related Investigative and Corrective 

Actions 

If any scribe line is found during any 

inspection required by paragraph (g)(1) of 

this AD: At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 

Alert Service Bulletin A3539, dated April 26, 

2013, except as specified in paragraphs (j)(1) 

and (j)(2) of this AD, do all applicable related 

investigative and corrective actions, by doing 

all applicable actions specified in the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3539, dated April 26, 

2013, except as specified in paragraph (j)(3) 

of this AD. 

(i) Surface Finish Restoration 

After completing any actions required by 

paragraph (h) of this AD: Before further 

flight, do surface finish restoration, in 

accordance with the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3539, dated April 26, 2013. 

(j) Exceptions to Paragraph (g) of this AD 

(1) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing 707 Alert Service Bulletin A3539, 

dated April 26, 2013, specifies a compliance 

time ‘‘after the original issue date of this 

service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(2) Where the Condition column of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 

Alert Service Bulletin A3539, dated April 26, 

2013, refers to total flight cycles ‘‘as of the 

original issue date of this service bulletin,’’ 

this AD applies to the airplanes with the 

specified total flight cycles as of the effective 

date of this AD. 

(3) Where Boeing 707 Alert Service 

Bulletin A3539, dated April 26, 2013, 

specifies to contact Boeing for additional 

inspections or repair instructions: Before 

further flight, repair the scribe line or 

cracking using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(k) 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 


emcdonald on DSK67QTVN1PROD with PROPOSALS
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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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