Federal Register / Vol. 80, No. 56 / Tuesday, March 24, 2015 / Proposed Rules 15525 

The Boeing Company: Docket No. FAA– 

2015–0495; Directorate Identifier 2014– 

NM–172–AD. 

(a) Comments Due Date 

We must receive comments by May 8, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–300, –400, and –500 series 

airplanes, certificated in any category, as 

identified in Boeing Alert Service Bulletin 

737–53A1328, dated July 22, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fatigue cracking at certain fastener locations 

in the window corners of the window belt 

area. We are issuing this AD to detect and 

correct fatigue cracking around the fastener 

locations that could cause multiple window 

corner skin cracks, which could result in 

rapid decompression and loss of structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections 

At the applicable time specified in tables 

1 and 2 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1328, 

dated July 22, 2014, except as required by 

paragraph (i)(1) of this AD: Do external 

surface high frequency eddy current (HFEC) 

inspections for cracking of the skin at the 12 

fastener locations at the upper forward and 

lower aft corners of each window between 

station (STA) 360 and STA 540 and between 

STA 727 and STA 908, left-side and rightside of the fuselage, at and between stringers 

S–11 and S–13, and all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1328, dated July 22, 2014, except as 

required by paragraph (i)(2) of this AD. Do all 

applicable related investigative and 

corrective actions before further flight. 

Repeat the inspections at the applicable 

times specified in tables 1 and 2 of paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1328, dated July 22, 2014, 

until the terminating action specified in 

paragraph (h) of this AD is done. 

(h) Optional Preventive Modification 

Accomplishment of a preventive 

modification in the fastener locations in the 

window corners of the window belt area 

between station (STA) 360 and STA 540 and 

between STA 727 and STA 908, left-side and 

right-side fuselage, at and between stringers 

S–11 and S–13, terminates the inspections 

required by paragraph (g) of this AD at the 

modified location only. The modification, 

including all applicable related investigative 

and corrective actions, must be done in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1328, dated July 22, 

2014, except as required by paragraph (i)(2) 

of this AD. 

(i) Exceptions to the Service Bulletin 

Specifications 

(1) Where Boeing Alert Service Bulletin 

737–53A1328, dated July 22, 2014, 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 Boeing Alert Service Bulletin 

737–53A1328, dated July 22, 2014, specifies 

to contact Boeing for repair instructions: 

Before further flight, repair the cracking 

using a method approved in accordance with 

the procedures specified in paragraph (j) of 

this AD. 

(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)(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) If any service information contains 

steps that are identified as RC (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

identified as RC are recommended. Those 

steps that are not identified as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the steps 

identified as RC can be done and the airplane 

can be put back in a serviceable condition. 

Any substitutions or changes to steps 

identified as RC require approval of an 

AMOC. 

(4) 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 Haytham Alaidy, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6447; fax: 425– 

917–6590; email: haytham.alaidy@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 the referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

Issued in Renton, Washington, on March 

13, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–06574 Filed 3–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0493; Directorate 

Identifier 2014–NM–184–AD] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics 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 certain 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company Model 

188 series airplanes. This proposed AD 

was prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the upper and lower 

wing skin planks at the attachment of 

the main landing gear (MLG) ribs at 

certain wing-stations are subject to 

widespread fatigue damage (WFD). This 

proposed AD would require an 

inspection (for cracking) and 

modification of the chordwise fastener 

rows of the upper and lower wing 

planks at the attachments to the MLG 

ribs at certain wing-stations. We are 

proposing this AD to prevent fatigue 

cracking of the upper and lower wing 

skin planks at the attachment of the 

MLG ribs, which could result in failure 

of the wing. 

DATES: We must receive comments on 

this proposed AD by May 8, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
15526 Federal Register / Vol. 80, No. 56 / Tuesday, March 24, 2015 / Proposed Rules 

• 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 Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company, Airworthiness 

Office, Dept. 6A0M, Zone 0252, Column 

P–58, 86 S. Cobb Drive, Marietta, GA 

30063; telephone 770–494–5444; fax 

770–494–5445; email ams.portal@

lmco.com; Internet http://

www.lockheedmartin.com/ams/tools/

TechPubs.html. 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–2015– 

0493; 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: Carl 

Gray, Aerospace Engineer, Airframe 

Branch, ACE–117A, FAA, Atlanta 

Aircraft Certification Office (ACO), 1701 

Columbia Avenue, College Park, GA 

30337; phone: 404–474–5554; fax: 404– 

474–5605; email: Carl.W.Gray@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– 

2015–0493; Directorate Identifier 2014– 

NM–184–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 

Structural fatigue damage is 

progressive. It begins as minute cracks, 

and those cracks grow under the action 

of repeated stresses. This can happen 

because of normal operational 

conditions and design attributes, or 

because of isolated situations or 

incidents such as material defects, poor 

fabrication quality, or corrosion pits, 

dings, or scratches. Fatigue damage can 

occur locally, in small areas or 

structural design details, or globally. 

Global fatigue damage is general 

degradation of large areas of structure 

with similar structural details and stress 

levels. Multiple-site damage is global 

damage that occurs in a large structural 

element such as a single rivet line of a 

lap splice joining two large skin panels. 

Global damage can also occur in 

multiple elements such as adjacent 

frames or stringers. Multiple-sitedamage and multiple-element-damage 

cracks are typically too small initially to 

be reliably detected with normal 

inspection methods. Without 

intervention, these cracks will grow, 

and eventually compromise the 

structural integrity of the airplane, in a 

condition known as WFD. As an 

airplane ages, WFD will likely occur, 

and will certainly occur if the airplane 

is operated long enough without any 

intervention. 

The FAA’s WFD final rule (75 FR 

69746, November 15, 2010) became 

effective on January 14, 2011. The WFD 

rule requires certain actions to prevent 

structural failure due to WFD 

throughout the operational life of 

certain existing transport category 

airplanes and all of these airplanes that 

will be certificated in the future. For 

existing and future airplanes subject to 

the WFD rule, the rule requires that 

DAHs establish a limit of validity (LOV) 

of the engineering data that support the 

structural maintenance program. 

Operators affected by the WFD rule may 

not fly an airplane beyond its LOV, 

unless an extended LOV is approved. 

The WFD rule (75 FR 69746, 

November 15, 2010) does not require 

identifying and developing maintenance 

actions if the DAHs can show that such 

actions are not necessary to prevent 

WFD before the airplane reaches the 

LOV. Many LOVs, however, do depend 

on accomplishment of future 

maintenance actions. As stated in the 

WFD rule, any maintenance actions 

necessary to reach the LOV will be 

mandated by airworthiness directives 

through separate rulemaking actions. 

In the context of WFD, this action is 

necessary to enable DAHs to propose 

LOVs that allow operators the longest 

operational lives for their airplanes, and 

still ensure that WFD will not occur. 

This approach allows for an 

implementation strategy that provides 

flexibility to DAHs in determining the 

timing of service information 

development (with FAA approval), 

while providing operators with certainty 

regarding the LOV applicable to their 

airplanes. 

This proposed AD was prompted by 

an evaluation by the DAH indicating 

that the upper and lower wing skin 

planks at the attachment of the MLG 

ribs are subject to WFD. The root cause 

of WFD is fatigue cracks manifesting 

and growing simultaneously at similar 

structural details and stress levels of the 

upper and lower wing skin planks at the 

attachment of the MLG ribs. Fatigue 

cracking is increasingly likely as the 

airplane is operated and aged, and 

without intervention, fatigue cracking of 

the upper and lower wing skin planks 

at the attachment of the MLG ribs could 

result in failure of the wing. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Lockheed Martin Electra 

88 Service Bulletin 721, dated April 30, 

2014. This service bulletin describes 

procedures to do a bolt hole eddy 

current (BHEC) inspection for cracking 

and modification of the chordwise 

fastener rows of the upper and lower 

wing planks at the attachments to the 

MLG ribs at wing-station (WS) 167 and 

WS 209 by removing the original 

fasteners and replacing them with new 

first oversize fasteners of the same type 

or approved substitute type for original 

fasteners. Corrective actions include 

repairing any cracking before further 

flight. The compliance times for the 

inspection and modification are 

specified at the following times. 

• For WS 167 lower: Before the 

accumulation of 33,300 total flight 

hours. 

• For WS 167 upper: Before the 

accumulation of 23,200 total flight 

hours. 

• For WS 209 lower: Before the 

accumulation of 31,500 total flight 

hours. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 56 / Tuesday, March 24, 2015 / Proposed Rules 15527 

• For WS 209 upper: Before the 

accumulation of 35,400 total flight 

hours. 

This service information is reasonably 

available; see ADDRESSES for ways to 

access this service information. 

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 these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between this Proposed AD 

and the Service Information.’’ 

Differences Between This Proposed AD 

and the Service Information 

Operators should note that, although 

the Accomplishment Instructions of 

Lockheed Martin Electra 88 Service 

Bulletin 721, dated April 30, 2014, 

describe procedures for reporting any 

damage detected to the manufacturer, 

this proposed AD would not require 

those actions. 

Although Lockheed Martin Electra 

Service Bulletin 88/721, dated April 30, 

2014, 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. 

Explanation of Compliance Time 

The compliance time for the 

modification specified in this proposed 

AD for addressing WFD was established 

to ensure that discrepant structure is 

modified before WFD develops in 

airplanes. Standard inspection 

techniques cannot be relied on to detect 

WFD before it becomes a hazard to 

flight. We will not grant any extensions 

of the compliance time to complete any 

AD-mandated service bulletin related to 

WFD without extensive new data that 

would substantiate and clearly warrant 

such an extension. 

Costs of Compliance 

We estimate that this proposed AD 

affects 4 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 

Cost on U.S. 

operators 

Inspection and Modification ............................ 560 work-hours × $85 per hour = $47,600 .... $5,000 $52,600 $210,400 

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): 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company: Docket 

No. FAA–2015–0493; Directorate 

Identifier 2014–NM–184–AD. 

(a) Comments Due Date 

We must receive comments by May 8, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Lockheed Martin 

Corporation/Lockheed Martin Aeronautics 

Company Model 188A and 188C airplanes, 

certificated in any category, serial numbers 

1001 and subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder (DAH) indicating 

that the upper and lower wing skin planks 

at the attachment of the main landing gear 

(MLG) ribs at certain wing-stations are 

subject to widespread fatigue damage (WFD). 

We are issuing this AD to prevent fatigue 

cracking of the upper and lower wing skin 

planks at the attachment of the MLG ribs, 

which could result in failure of the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
15528 Federal Register / Vol. 80, No. 56 / Tuesday, March 24, 2015 / Proposed Rules 

(g) Inspection, Modification, and Corrective 

Action 

At the later of the times specified in 

paragraphs (g)(1) and (g)(2) of this AD: 

Remove the chordwise fastener rows of the 

upper and lower wing planks at the 

attachments to the MLG ribs at wing-station 

(WS) 167 and WS 209; do a bolt hole eddy 

current (BHEC) inspection to detect cracking 

of the fastener rows; and replace the original 

fasteners with new, first oversize fasteners; in 

accordance with the Accomplishment 

Instructions of Lockheed Martin Electra 88 

Service Bulletin 721, dated April 30, 2014. If 

any cracking is found during any inspection 

required by this paragraph: Before further 

flight, repair the cracking, in accordance with 

the Accomplishment Instructions of 

Lockheed Martin Electra 88 Service Bulletin 

721, dated April 30, 2014. 

(1) At the applicable time specified in table 

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

Lockheed Martin Electra 88 Service Bulletin 

721, dated April 30, 2014. Where table 1 of 

paragraph 1.E., ‘‘Compliance,’’ of Lockheed 

Martin Electra 88 Service Bulletin 721, dated 

April 30, 2014, specifies ‘‘Flt. Hrs,’’ this AD 

specifies ‘‘total flight hours.’’ 

(2) Within 365 days or 600 flight hours 

after the effective date of this AD, whichever 

occurs first. 

(h) No Reporting 

Although Lockheed Martin Electra 88 

Service Bulletin 721, dated April 30, 2014, 

specifies to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta 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 (j)(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. 

(j) Related Information 

(1) For more information about this AD, 

Carl Gray, Aerospace Engineer, Airframe 

Branch, ACE–117A, FAA, Atlanta ACO, 1701 

Columbia Avenue, College Park, GA 30337; 

phone: 404–474–5554; fax: 404–474–5605; 

email: carl.w.gray@faa.gov. 

(2) For service information identified in 

this AD, contact Lockheed Martin 

Corporation/Lockheed Martin Aeronautics 

Company, Airworthiness Office, Dept. 6A0M, 

Zone 0252, Column P–58, 86 S. Cobb Drive, 

Marietta, GA 30063; telephone 770–494– 

5444; fax 770–494–5445; email 

ams.portal@lmco.com; Internet http:// 

www.lockheedmartin.com/ams/tools/ 

TechPubs.html. 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 March 

12, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–06576 Filed 3–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0492; Directorate 

Identifier 2014–NM–232–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

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 

Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702), 

CL–600–2D15 (Regional Jet Series 705), 

and CL–600–2D24 (Regional Jet Series 

900) airplanes. This proposed AD was 

prompted by reports of a disconnect 

between the elevator lever and control 

rod. This proposed AD would require 

replacement of left and right fixed 

control rods and lever assemblies of the 

elevator control system. We are 

proposing this AD to prevent a 

disconnect between the elevator lever 

and control rod, which could lead to uncommanded elevator movement of the 

associated control surface, a large 

difference between the position of the 

left and the right elevator control 

surface, and consequent reduced 

controllability of the airplane and 

degradation of the structural integrity of 

the horizontal stabilizer. 

DATES: We must receive comments on 

this proposed AD by May 8, 2015. 

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: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Bombardier, 

Inc., 400 Coˆte Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 

514–855–5000; fax 514–855–7401; email 

thd.crj@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. 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–2015– 

0492; 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 Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office (ACO), 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7318; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–0492; Directorate Identifier 

2014–NM–232–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 based on 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 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS