5730 Federal Register / Vol. 77, No. 24 / Monday, February 6, 2012 / Proposed Rules 

(e) Reason 

This AD was prompted by reports of an 

inoperative fire shut-off valve (FSOV) as a 

result of damage due to over-length of the 

bonding lead. We are issuing this AD to 

detect and correct contact or chafing of wires 

and bonding leads which, if not detected, 

could be a source of sparks in the wing 

trailing edge, and could lead to an 

uncontrolled engine fire. 

(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 of the FSOV Bonding Leads 

Within 4,500 flight hours or 30 months 

after the effective date of this AD, whichever 

occurs first: Do a one-time detailed 

inspection for length of the FSOV bonding 

leads, and for contact or chafing of the wires 

located on left hand (LH) side and right-hand 

(RH) side of the wing rear spar, in accordance 

with Accomplishment Instructions of the 

Airbus Mandatory Service Bulletin A300–24– 

0106, dated July 9, 2010 (for Model A300 

series airplanes); or Airbus Mandatory 

Service Bulletin A300–24–6108, dated July 9, 

2010 (for Model A300–600 series airplanes). 

(h) Corrective Action for FSOV Bonding 

Leads 

If, during the inspection required by 

paragraph (g) of this AD, the length of the 

bonding lead(s) is more than 80 mm (3.15 

inches), before further flight, replace the 

bonding lead(s) with a new bonding lead 

having a length equal to 80 mm (3.15 inches), 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–24–0106, dated July 9, 2010 

(for Model A300 series airplanes); or Airbus 

Mandatory Service Bulletin A300–24–6108, 

dated July 9, 2010 (for Model A300–600 

series airplanes). 

(i) Repair of the Wires of the LH and RH 

Sides 

If, during the inspection required by 

paragraph (g) of this AD, contact(s) or 

chafing(s) of the wires is found, repair the 

wires in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–24–0106, 

dated July 9, 2010 (for Model A300 series 

airplanes); or Airbus Mandatory Service 

Bulletin A300–24–6108, dated July 9, 2010 

(for Model A300–600 series airplanes). 

(j) Parts Installation 

As of the effective date of this AD, no 

person may install any bonding lead longer 

than 80 mm (3.15 inches), located between 

LH/RH engine hydraulic FSOV and wing rear 

spar in the zones 575/675 on any airplane. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

227–1149. 

(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. 

(l) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2011–0084, dated May 24, 2011; and the 

service information identified in paragraphs 

(l)(1), and (l)(2) of this AD; for related 

information. 

(1) Airbus Mandatory Service Bulletin 

A300–24–0106, dated July 9, 2010. 

(2) Airbus Mandatory Service Bulletin 

A300–24–6108, dated July 9, 2010. 

Issued in Renton, Washington, on January 

12, 2012. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–2625 Filed 2–3–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0042; Directorate 

Identifier 2011–NM–154–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 supersede an 

existing airworthiness directive (AD) 

that applies to 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. 

The existing AD currently requires a 

one-time inspection of the main landing 

gear (MLG) shock strut assemblies for 

part and serial numbers; for certain 

MLG shock strut assemblies, a one-time 

inspection of the torque link apex joint, 

and corrective actions if necessary; and, 

for certain MLG shock strut assemblies, 

replacement or rework of the apex nut. 

Since we issued that AD, we have 

determined that part and serial numbers 

for MLG shock strut assemblies for 

Model CL–600–2D15 and CL–600–2D24 

airplanes were inadvertently omitted 

from certain requirements of the 

existing AD. This proposed AD would 

continue to require the actions in the 

existing AD, and would add the 

previously omitted part and serial 

numbers. We are proposing this AD to 

detect and correct improper assembly 

and damage of the MLG torque link 

apex joint, which could cause heavy 

vibration during landing, consequent 

damage to MLG components, and 

subsequent collapse of the MLG. 

DATES: We must receive comments on 

this proposed AD by March 22, 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., 400 Cote-Vertu Road West, Dorval, 

Quebec H4S 1Y9, Canada; phone: 514– 

855–5000; fax: 514–855–7401; email: 

thd.crj@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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 24 / Monday, February 6, 2012 / Proposed Rules 5731 

FOR FURTHER INFORMATION CONTACT: 

Stephen Kowalski, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; phone: (516) 228– 

7327; fax: (516) 794–5531; email: 

Stephen.Kowalski@faa.gov. 

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–2012–0042; Directorate Identifier 

2011–NM–154–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 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On March 23, 2011, we issued AD 

2011–08–04, Amendment 39–16654 (76 

FR 20498, April 13, 2011). That AD 

required actions intended to address an 

unsafe condition on 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. 

Since we issued AD 2011–08–04, 

Amendment 39–16654 (76 FR 20498, 

April 13, 2011), we have determined 

that part and serial numbers for main 

landing gear (MLG) shock strut 

assemblies for Model CL–600–2D15 

(Regional Jet Series 705) airplanes and 

Model CL–600–2D24 (Regional Jet 

Series 900) airplanes were inadvertently 

omitted from paragraphs (g) and (h) of 

that AD. As a result, operators could be 

inspecting for part and serial numbers 

which they do not have, and would, 

therefore, not be required to accomplish 

the actions intended to correct the 

identified unsafe condition on those 

airplanes. Therefore, we have removed 

airplanes identified in paragraph (c)(2) 

of this AD from the requirements of 

paragraphs (g), (h), and (i) of this AD. 

We have added new requirements for 

those airplanes to inspect for the 

appropriate part numbers and serial 

numbers, and to do all applicable 

inspections and corrective actions. 

AD 2011–08–04, Amendment 39– 

16654 (76 FR 20498, April 13, 2011), 

referred to Transport Canada Civil 

Aviation (TCCA) (the aviation authority 

for Canada) Airworthiness Directive CF– 

2009–20, dated May 1, 2009 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

There have been four reports of loose or 

detached main landing gear torque link apex 

pin locking plate and the locking plate 

retainer bolt. This condition could result in 

torque link apex pin disengagement, heavy 

vibration during landing, damage to main 

landing gear components and subsequent 

main landing gear collapse. 

Investigation has determined that incorrect 

stack-up tolerances of the apex joint or 

improper installation of the locking plate and 

apex nut could result in torque link apex pin 

disengagement. This [TCCA] directive 

mandates [a one-time detailed] inspection of 

the torque link apex joint [for correct 

installation and damage, and corrective 

actions if necessary] and replacement of the 

torque link apex nut. 

The corrective actions include reinstalling parts that are not correctly 

installed and replacing damaged parts. 

You may obtain further information by 

examining the MCAI in the AD docket. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

The MCAI specifies to inspect only 

airplanes having certain serial numbers 

that are part of the MCAI applicability. 

Because the affected part could be 

rotated onto any of the airplanes listed 

in the applicability, this proposed AD 

would continue to require that the 

inspection be done on all airplanes. We 

have coordinated this with the TCCA. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 361 products of U.S. 

registry. 

The actions required by AD 2011–08– 

04, Amendment 39–16654 (76 FR 

20498, April 13, 2011), and retained in 

this proposed AD that about 5 workhours per product, at an average labor 

rate of $85 per work hour. Based on 

these figures, the estimated cost of the 

currently required actions is $153,425, 

or $425 per product. 

We estimate that it would take about 

5 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$153,425, or $425 per product. 

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); 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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
5732 Federal Register / Vol. 77, No. 24 / Monday, February 6, 2012 / Proposed Rules 

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 

removing Amendment 39–16654 (76 FR 

20498, April 13, 2011) and adding the 

following new AD: 

Bombardier, Inc.: Docket No. FAA–2012– 

0042; Directorate Identifier 2011–NM– 

154–AD. 

(a) Comments Due Date 

We must receive comments by March 22, 

2012. 

(b) Affected ADs 

This AD supersedes AD 2011–08–04, 

Amendment 39–16654 (76 FR 20498, April 

13, 2011). 

(c) Applicability 

This AD applies to the Bombardier 

airplanes identified in paragraphs (c)(1) and 

(c)(2) of this AD, certificated in any category. 

(1) Model CL–600–2C10 (Regional Jet 

Series 700, 701 & 702) airplanes, serial 

numbers (S/Ns) 10003 and subsequent. 

(2) Model CL–600–2D15 (Regional Jet 

Series 705) airplanes and Model CL–600– 

2D24 (Regional Jet Series 900) airplanes, 

S/Ns 15001 and subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32: Landing gear. 

(e) Reason 

This AD was prompted by reports of loose 

or detached main landing gear (MLG) torque 

link apex pin locking plate and the locking 

plate retainer bolt in the torque link apex 

joint. We are issuing this AD to detect and 

correct improper assembly and damage of the 

MLG torque link apex joint, which could 

cause heavy vibration during landing, 

consequent damage to MLG components, and 

subsequent collapse of the MLG. 

(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. 

Restatement of Requirements of AD 2011– 

08–04, Amendment 39–16654 (76 FR 20498, 

April 13, 2011) 

(g) Inspection for Part Number (P/N) and 

Serial Number (S/N) for Model CL–600–2C10 

Airplanes 

For airplanes identified in paragraph (c)(1) 

of this AD: Within 900 flight hours after May 

18, 2011 (the effective date of AD 2011–08– 

04, Amendment 39–16654 (76 FR 20498, 

April 13, 2011)), inspect the main landing 

gear (MLG) shock strut assemblies to 

determine whether an MLG shock strut 

assembly having P/Ns 49000–11 through 

49000–22 inclusive and a S/N 0001 through 

0284 inclusive is installed. A review of 

airplane maintenance records is acceptable in 

lieu of this inspection if the part and serial 

numbers of the MLG shock strut assembly 

can be conclusively determined from that 

review. 

(h) Inspection of the Torque Link Apex Joint 

for Model CL–600–2C10 Airplanes 

For any MLG shock strut assembly having 

P/Ns 49000–11 through 49000–22 inclusive 

and a S/N 0001 through 0284 inclusive found 

installed during the inspection or records 

check required by paragraph (g) of this AD: 

Within 900 flight hours after May 18, 2011, 

perform a one-time detailed inspection and 

all applicable corrective actions on the torque 

link apex joint, in accordance with Part A of 

the Accomplishment Instructions of 

Bombardier Service Bulletin 670BA–32–019, 

Revision A, dated September 18, 2008, 

except as provided by paragraph (o) of this 

AD. Do all applicable corrective actions 

before further flight. 

(i) Replacement or Rework of the Apex Nut 

for Model CL–600–2C10 Airplanes 

For any MLG shock strut assembly 

identified during the inspection or records 

check required by paragraph (g) of this AD: 

Within 4,500 flight hours after May 18, 2011, 

replace or rework the apex nut, in accordance 

with Part B of the Accomplishment 

Instructions of Bombardier Service Bulletin 

670BA–32–019, Revision A, dated September 

18, 2008. 

(j) Parts Installation 

For all airplanes: As of May 18, 2011, no 

person may install, on any airplane, a 

replacement MLG shock strut assembly 

identified in paragraph (j)(1) or (j)(2) of this 

AD, unless it has been reworked in 

accordance with paragraph B. of Part B of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–019, Revision A, 

dated September 18, 2008. 

(1) Part numbers 49000–11 through 49000– 

22 inclusive, and with a serial number in the 

range of S/Ns 0001 through 0284 inclusive 

(the serial number can start with ‘‘MA,’’ 

‘‘MAL,’’ or ‘‘MA–’’). 

(2) Part numbers 49050–5 through 49050– 

10 inclusive, and with a serial number in the 

range of S/Ns 1001 through 1114 inclusive 

(the serial number can start with ‘‘MA,’’ 

‘‘MAL,’’ or ‘‘MA–’’). 

New Requirements of This AD 

(k) Inspection for Part Number and Serial 

Number for Model CL–600–2D15 and CL– 

600–2D24 Airplanes 

For airplanes identified in paragraph (c)(2) 

of this AD: Within 900 flight hours after the 

effective date of this AD, inspect the MLG 

shock strut assemblies to determine whether 

an MLG shock strut assembly having P/Ns 

49050–5 through 49050–10 inclusive and a 

S/N 0001 through 1114 inclusive is installed. 

A review of airplane maintenance records is 

acceptable in lieu of this inspection if the 

part and serial numbers of the MLG shock 

strut assembly can be conclusively 

determined from that review. 

(l) Inspection of the Torque Link Apex Joint 

for Model CL–600–2D15 and CL–600–2D24 

Airplanes 

For any MLG shock strut assembly having 

P/Ns 49050–5 through 49050–10 inclusive 

and a S/N 0001 through 1114 inclusive found 

installed during the inspection or records 

check required by paragraph (k) of this AD: 

Within 900 flight hours after the effective 

date of this AD, perform a one-time detailed 

inspection and all applicable corrective 

actions on the torque link apex joint, in 

accordance with Part A of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–019, Revision A, 

dated September 18, 2008, except as 

provided by paragraph (o) of this AD. Do all 

applicable corrective actions before further 

flight. 

(m) Replacement or Rework of the Apex Nut 

for Model CL–600–2D15 and CL–600–2D24 

Airplanes 

For any MLG shock strut assembly 

identified during the inspection or records 

check required by paragraph (k) of this AD: 

Within 900 flight hours after the effective 

date of this AD, replace or rework the apex 

nut, in accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–019, Revision A, 

dated September 18, 2008. 

(n) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

Inspections, corrective actions, 

replacements, and rework accomplished 

before the effective date of this AD, in 

accordance with Bombardier Service Bulletin 

670BA–32–019, dated March 16, 2006, are 

considered acceptable for compliance with 

the corresponding actions specified in this 

AD. 

(o) Inspections Not Required Under Certain 

Conditions 

The inspections specified in paragraph (h) 

or (l) of this AD are not required if the actions 

specified in paragraph (i) or (m) of this AD, 

as applicable, have already been 

accomplished; or if Bombardier Repair 

Engineering Order 670–32–11–0022, dated 

October 22, 2005, or Goodrich Service 

Concession Request SCR 0056–05, dated 

October 22, 2005; has been incorporated. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 24 / Monday, February 6, 2012 / Proposed Rules 5733 

(p) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7300; fax (516) 

794–5531. 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. 

(q) Special Flight Permits 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(r) Related Information 

Refer to MCAI Canadian Airworthiness 

Directive CF–2009–20, dated May 1, 2009; 

and Bombardier Service Bulletin 670BA–32– 

019, Revision A, dated September 18, 2008; 

for related information. 

Issued in Renton, Washington, on January 

24, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–2619 Filed 2–3–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

Docket No. FAA–2011–1407; Airspace 

Docket No. 11–AGL–25 

RIN 2120–AA66 

Proposed Modification of Area 

Navigation (RNAV) Route Q–62; 

Northeast United States 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

modify area navigation (RNAV) route 

Q–62 by extending it further west and 

incorporating two additional navigation 

fixes. The route extension is proposed to 

link two RNAV Standard Terminal 

Arrival Routes (STARs) serving the 

Chicago O’Hare International Airport, 

IL, terminal area with the high altitude 

route. The FAA is taking this action to 

increase National Airspace System 

(NAS) efficiency and enhance flight 

safety as aircraft transition from the en 

route airway structure to the terminal 

area airspace phase of flight. 

DATES: Comments must be received on 

or before March 22, 2012. 

ADDRESSES: Send comments on this 

proposal to the U.S. Department of 

Transportation, Docket Operations, M– 

30, 1200 New Jersey Avenue SE., West 

Building Ground Floor, Room W12–140, 

Washington, DC 20590–0001; telephone: 

(202) 366–9826. You must identify FAA 

Docket No. FAA–2011–1407 and 

Airspace Docket No. 11–AGL–25 at the 

beginning of your comments. You may 

also submit comments through the 

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

FOR FURTHER INFORMATION CONTACT: 

Colby Abbott, Airspace, Regulations and 

ATC Procedures Group, Office of 

Airspace Services, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone: (202) 267–8783. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested parties are invited to 

participate in this proposed rulemaking 

by submitting such written data, views, 

or arguments as they may desire. 

Comments that provide the factual basis 

supporting the views and suggestions 

presented are particularly helpful in 

developing reasoned regulatory 

decisions on the proposal. Comments 

are specifically invited on the overall 

regulatory, aeronautical, economic, 

environmental, and energy-related 

aspects of the proposal. 

Communications should identify both 

docket numbers (FAA Docket No. FAA– 

2011–1407 and Airspace Docket No. 11– 

AGL–25) and be submitted in triplicate 

to the Docket Management Facility (see 

ADDRESSES section for address and 

phone number). You may also submit 

comments through the Internet at 

http://www.regulations.gov. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

on this action must submit with those 

comments a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to FAA 

Docket No. FAA–2011–1407 and 

Airspace Docket No. 11–AGL–25.’’ The 

postcard will be date/time stamped and 

returned to the commenter. 

All communications received on or 

before the specified closing date for 

comments will be considered before 

taking action on the proposed rule. The 

proposal contained in this action may 

be changed in light of comments 

received. All comments submitted will 

be available for examination in the 

public docket both before and after the 

closing date for comments. A report 

summarizing each substantive public 

contact with FAA personnel concerned 

with this rulemaking will be filed in the 

docket. 

Availability of NPRMs 

An electronic copy of this document 

may be downloaded through the 

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

Recently published rulemaking 

documents can also be accessed through 

the FAA’s Web page at http:// 

www.faa.gov/airports_airtraffic/ 

air_traffic/publications/ 

airspace_amendments/. 

You may review the public docket 

containing the proposal, any comments 

received and any final disposition in 

person in the Dockets Office (see 

ADDRESSES section for address and 

phone number) between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. An informal docket 

may also be examined during normal 

business hours at the office of the 

Central Service Center, Operations 

Support Group, Federal Aviation 

Administration, 2601 Meacham Blvd., 

Fort Worth, TX 76137. 

Persons interested in being placed on 

a mailing list for future NPRMs should 

contact the FAA’s Office of Rulemaking, 

(202) 267–9677, for a copy of Advisory 

Circular No. 11–2A, Notice of Proposed 

Rulemaking Distribution System, which 

describes the application procedure. 

The Proposal 

The FAA is proposing an amendment 

to Title 14, Code of Federal Regulations 

(14 CFR) part 71 by extending high 

altitude RNAV route Q–62 to the west 

to include the WATSN and DAIFE fixes. 

The proposed change would facilitate 

linking the WATSN and HALIE RNAV 

STARs serving Chicago O’Hare 

International Airport, IL, with the high 

altitude route and establish a seamless 

transition for westbound air traffic from 

the New York metropolitan area into the 

Chicago O’Hare International Airport, 

IL, terminal area. This proposed route 

extension would also reduce ATC 

system complexity, air traffic controller 

and pilot workload, and voice 

communication requirements, as well as 


tkelley on DSK3SPTVN1PROD with PROPOSALS