16188 Federal Register / Vol. 77, No. 54 / Tuesday, March 20, 2012 / Proposed Rules 

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); and 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 AD: 

Dassault Aviation: Docket No. FAA–2012– 

0269; Directorate Identifier 2011–NM– 

105–AD. 

(a) Comments Due Date 

We must receive comments by May 4, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Dassault Aviation 

Model FALCON 7X airplanes, certificated in 

any category, serial numbers 3, 10, 13, 18, 19, 

20, 22, 23, 24, 26, 27, 29, 30, 31, 32, 33, 35, 

36, 38, 41, 42, 43, 47, 48, 58, 63, 64, 66, 67, 

68, 71, 76, 78, 79, 83, 84, 85, 86, 87, and 93; 

except for airplanes on which the Dassault 

Aviation modification specified in Dassault 

Mandatory Service Bulletin 7X–174, has been 

incorporated. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 35: Oxygen. 

(e) Reason 

This AD was prompted by a report that a 

passenger oxygen pipe at frame 10 was 

chafing against the forward lavatory rear 

structure, raising the risk of the oxygen pipe 

developing a crack. We are issuing this AD 

to prevent rupture of the oxygen pipe which, 

in case of a cabin depressurization, would 

impair operation of the passenger oxygen 

distribution system. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspection 

Within 2 months after the effective date of 

this AD, do a boroscope inspection of the 

passenger oxygen pipe for clearance and a 

general visual inspection for damage of the 

oxygen pipe, in accordance with the 

Accomplishment Instructions of Dassault 

Mandatory Service Bulletin 7X–174, dated 

March 10, 2011. 

(h) Corrective Actions 

If during any inspection required by 

paragraph (g) of this AD any damage is found 

or oxygen pipe clearance is less than 3 

millimeters (mm) (0.12 inch): Before further 

flight, modify the oxygen pipe routing, 

including doing a general visual inspection 

for chafing of the pipe and doing all 

applicable replacements, in accordance with 

the Accomplishment Instructions of Dassault 

Mandatory Service Bulletin 7X–174, dated 

March 10, 2011. 

(i) Oxygen Pipe Routing Modification 

If, during any inspection required by 

paragraph (g) of this AD, oxygen pipe 

clearance is 3 mm (0.12 inch) or more but 

less than 12 mm (0.47 inch): Within 98 

months or 4,000 flight cycles after the 

effective date of this AD, whichever occurs 

first, modify the routing of the passenger 

oxygen pipe, including doing a general visual 

inspection for chafing of the pipe and doing 

all applicable replacements, in accordance 

with the Accomplishment Instructions of 

Dassault Mandatory Service Bulletin 7X–174, 

dated March 10, 2011. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1137; 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 or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(k) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2011–0070, dated April 18, 2011; and 

Dassault Mandatory Service Bulletin 7X–174, 

Initial Issuance, dated March 10, 2011; for 

related information. 

Issued in Renton, Washington, on March 9, 

2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–6627 Filed 3–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0268; Directorate 

Identifier 2011–NM–129–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 certain 

The Boeing Company Model 737–600, 

–700, –700C, –800, and –900 series 

airplanes. This proposed AD was 

prompted by reports of incorrectly 

installed bolts common to the rear spar 

termination fitting on the horizontal 

stabilizer. This proposed AD would 

require inspecting for a serial number 

that starts with the letters ‘‘SAIC’’ on the 

left- and right-side horizontal stabilizer 

identification plate; a detailed 

inspection for correct bolt protrusion 

and chamfer of the termination fitting 

bolts of the horizontal stabilizer rear 

spar, if necessary; inspecting to 

determine if certain bolts are installed, 

if necessary, and related investigative 

and corrective actions if necessary. This 

proposed AD would also require 


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repetitive inspections for cracking of the 

termination fitting at certain bolt 

locations, and repair if necessary. We 

are proposing this AD to prevent loss of 

structural integrity of the horizontal 

stabilizer attachment and loss of control 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 4, 2012. 

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 Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; email 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

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

Washington 98057–3356; phone: 425– 

917–6440; fax: 425–917–6590; email: 

nancy.marsh@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– 

2012–0268; Directorate Identifier 2011– 

NM–129–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 reports of incorrectly 

installed bolts common to the rear spar 

terminal fitting of the horizontal 

stabilizer. During manufacturing, the 

termination fitting bolts were installed 

without proper thread protrusion due to 

missing washers. This resulted in an 

unclamped condition between the 

horizontal stabilizer rear spar and the 

termination fitting. Loose bolts attaching 

the horizontal stabilizer termination 

fitting can lead to premature cracking of 

the fitting. This condition, if not 

corrected, could result in the loss of 

structural integrity of the horizontal 

stabilizer attachment and loss of control 

of the airplane. 

Relevant Service Information 

We reviewed Boeing Service Bulletin 

737–55–1090, dated March 30, 2011. 

This service information describes 

procedures for inspecting for a serial 

number that starts with the letters 

‘‘SAIC’’ on the left- and right-side 

horizontal stabilizer identification plate; 

a detailed inspection for correct bolt 

protrusion and chamfer of the 

termination fitting fasteners of the 

horizontal stabilizer rear spar, if 

necessary; an inspection to determine if 

certain bolts are installed, if necessary, 

and related investigative and corrective 

actions if necessary. This service 

information also describes procedures 

for repetitive high frequency eddy 

current (HFEC) and ultrasonic (UT) 

inspections for cracking of the 

termination fitting at certain bolt 

locations, and repair if necessary. 

The related investigative action is a 

detailed inspection for damage 

(including chafing, galling, nicks, 

gouges, and exposed bare metal) of the 

bolt shank. The corrective action 

includes installing new hardware, 

replacing the bolt with a new bolt, and 

contacting The Boeing Company for 

repair instructions and doing the repair. 

The initial compliance time for 

certain airplanes is before 32,000 total 

flight cycles or within 12 months after 

the original issue date of the service 

information. For certain other airplanes, 

the initial compliance time is before 

36,000 total flight cycles or within 12 

months after the original issue date of 

the 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 the Proposed AD 

and the Service Information.’’ 

Differences Between the Proposed AD 

and the Service Information 

Boeing Service Bulletin 737–55–1090, 

dated March 30, 2011, does not specify 

doing an inspection for bolt type. This 

proposed AD would require inspection 

for correct bolt type. If incorrect bolt 

type is found, paragraph (k) of this 

proposed AD would require repair using 

a method approved in accordance with 

paragraph (l). 

Figure 1 of Boeing Service Bulletin 

737–55–1090, dated March 30, 2011, 

contains an error. The illustration of an 

identification plate that points to the 

location of a part number should point 

to the serial number and the example 

‘‘SAIC 1234’’ should be located on the 

serial number line. This proposed AD 

requires an inspection for an 

identification plate with a serial number 

that starts with the letters ‘‘SAIC.’’ 

Boeing Service Bulletin 737–55–1090, 

dated March 30, 2011, specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, 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 


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we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

affects 373 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 ......................................... 1 work-hour × $85 per hour = $85 per inspection 

cycle.

$0 $85 $31,705 

Replacement of bolts ....................... 17 work-hours × $85 per hour = $1,445 ...................... 1,530 2,975 1,109,675 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

(contacting Boeing and repairing cracks 

or damage) specified in this AD. 

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: 

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– 

2012–0268; Directorate Identifier 2011– 

NM–129–AD. 

(a) Comments Due Date 

We must receive comments by May 4, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

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

series airplanes, certificated in any category, 

as identified in Boeing Service Bulletin 737– 

55–1090, dated March 30, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 55: Stabilizer. 

(e) Unsafe Condition 

This AD was prompted by reports of 

incorrectly installed bolts common to the rear 

spar termination fitting of the horizontal 

stabilizer. We are issuing this AD to prevent 

loss of structural integrity of the horizontal 

stabilizer attachment and loss of control of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspecting the Horizontal Stabilizer and 

Corrective Actions 

Except as provided by paragraph (i) of this 

AD, at the applicable times specified in 

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

Service Bulletin 737–55–1090, dated March 

30, 2011: Do an inspection for a serial 

number that starts with the letters ‘‘SAIC’’ on 

the identification plates of the left- and rightside horizontal stabilizers, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 737–55–1090, dated 

March 30, 2011. 

(1) If a serial number starting with the 

letters ‘‘SAIC’’ is found on a horizontal 

stabilizer identification plate: Except as 

provided by paragraph (i) of this AD, at the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–55–1090, dated March 30, 2011, do a 

detailed inspection for correct bolt protrusion 

and correct chamfer of the termination fitting 

bolts of the horizontal stabilizer rear spar, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

55–1090, dated March 30, 2011. Concurrently 

with the detailed inspection, inspect to 

determine if bolts other than part number (P/ 

N) BACB30US14K() or BACB30US16K(), as 

applicable, are installed. Before further flight, 

do all applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–55–1090, dated March 

30, 2011. 

(2) If no SAIC serial number is found, no 

further action is required by this AD. 

(h) High Frequency Eddy Current and 

Ultrasonic Inspections of Termination 

Fitting and Repair 

For any location where a new bolt having 

a P/N BACB30US14K() is installed due to 

damage found during any inspection 

required by paragraph (g) of this AD: Except 

as provided by paragraph (i) of this AD, at 

the times specified in paragraph 1.E., 


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‘‘Compliance,’’ of Boeing Service Bulletin 

737–55–1090, dated March 30, 2011, do 

HFEC and ultrasonic inspections for cracking 

of the forward and aft sides of the 

termination fitting, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–55–1090, dated March 

30, 2011. If any crack is found in any 

termination fitting: Before further flight, 

repair in accordance with the procedures 

specified in paragraph (l) of this AD. Repeat 

the HFEC and ultrasonic inspections 

thereafter at intervals not to exceed 3,500 

flight cycles. 

(i) Exception to Compliance Time 

Where Boeing Service Bulletin 737–55– 

1090, dated March 30, 2011, specifies a 

compliance time ‘‘after the original issue date 

on the service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(j) Exception to Service Bulletin 

Where Figure 1 of Boeing Service Bulletin 

737–55–1090, dated March 30, 2011, points 

to the location of a part number rather than 

the serial number, this AD requires an 

inspection for an identification plate with a 

serial number that starts with the letters 

‘‘SAIC.’’ 

(k) Exceptions to Corrective Actions 

If, during any inspection required by 

paragraphs (g) and (h) of this AD, any bolts 

other than P/N BACB30US14K() or 

BACB30US16K(), as applicable, are found: 

Before further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (l) of this AD. 

(l) 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 the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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. 

(m) Related Information 

(1) For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6440; fax: 425–917– 

6590; email: nancy.marsh@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, Washington 98124–2207; telephone 

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

5680; email me.boecom@boeing.com; Internet 

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

review copies of the 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 March 8, 

2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–6628 Filed 3–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0267; Directorate 

Identifier 2011–NM–174–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 DHC–8–400 

series airplanes. This proposed AD was 

prompted by reports that the automatic 

de-icing mode became unavailable due 

to a failure of the timer and monitor unit 

(TMU). This proposed AD would 

require replacing the TMU. We are 

proposing this AD to prevent loss of the 

automatic de-icing mode and 

consequent increased workload for the 

flight crew, which, depending on 

additional failures, could lead to loss of 

control of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 4, 2012. 

ADDRESSES: You may send comments 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., Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; email 

thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

You may review copies of the 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office 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, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 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–2012–0267; Directorate Identifier 

2011–NM–174–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 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS