Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Proposed Rules 477 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

The Proposed Amendment 

In consideration of the foregoing, the 

Federal Aviation Administration 

proposes to amend part 25 of Title 14, 

Code of Federal Regulations, as follows: 

PART 25—AIRWORTHINESS 

STANDARDS: TRANSPORT 

CATEGORY AIRPLANES 

1. The authority citation for part 25 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701– 

44702, and 44704. 

2. Amend § 25.729 by revising 

paragraphs (a)(1)(ii), (a)(1)(iii), (a)(3), (b), 

(e) introductory text, (e)(5), (f) 

introductory text, and (f)(1), and by 

adding paragraphs (e)(7) and (f)(3) to 

read as follows: 

§ 25.729 Operating limitations. 

(a) * * * 

(1) * * * 

(ii) The combination of friction loads, 

inertia loads, brake torque loads, air 

loads, and gyroscopic loads resulting 

from the wheels rotating at a peripheral 

speed equal to 1.23 VSR (with the wingflaps in takeoff position at design takeoff 

weight), occurring during retraction and 

extension at any airspeed up to 1.5 VSR1

(with the wing-flaps in the approach 

position at design landing weight), and 

(iii) Any load factor up to those 

specified in § 25.345(a) for the wingflaps extended condition. 

* * * * * 

(3) Landing gear doors, their operating 

mechanism, and their supporting 

structures must be designed for the 

yawing maneuvers prescribed for the 

airplane in addition to the conditions of 

airspeed and load factor presented in 

paragraphs (a)(1) and (2) of this section. 

(b) Landing gear lock. There must be 

positive means to keep the landing gear 

extended in flight and on the ground. 

There must be positive means to keep 

the landing gear and doors in the correct 

retracted position in flight, unless it can 

be shown that lowering of the landing 

gear or doors, or flight with the landing 

gear or doors extended, at any speed, is 

not hazardous. 

* * * * * 

(e) Position indicator and warning 

device. If a retractable landing gear is 

used, there must be a landing gear 

position indicator easily visible to the 

pilot or to the appropriate crew 

members (as well as necessary devices 

to actuate the indicator) to indicate 

without ambiguity that the retractable 

units and their associated doors are 

secured in the extended (or retracted) 

position. The means must be designed 

as follows: 

* * * * * 

(5) The system used to generate the 

aural warning must be designed to 

minimize false or inappropriate alerts. 

* * * * * 

(7) A clear indication or warning must 

be provided whenever the landing gear 

position is not consistent with the 

landing gear selector lever position. 

(f) Protection of equipment on landing 

gear and in wheel wells. Equipment that 

is essential to the safe operation of the 

airplane and that is located on the 

landing gear or in wheel wells must be 

protected from the damaging effects of— 

(1) A bursting tire; 

* * * * * 

(3) Possible wheel brake temperatures. 

3. Amend § 25.773 by revising 

paragraph (b)(2) and adding paragraphs 

(b)(3) and (b)(4) to read as follows: 

§ 25.773 Pilot compartment view. 

* * * * * 

(b) * * * 

(2) No single failure of the systems 

used to provide the view required by 

paragraph (b)(1) of this section may 

cause the loss of that view by both pilots 

in the specified precipitation 

conditions. 

(3) The first pilot must have a window 

that— 

(i) Is openable under the conditions 

prescribed in paragraph (b)(1) of this 

section when the cabin is not 

pressurized; 

(ii) Provides the view specified in 

paragraph (b)(1) of this section; and 

(iii) Provides sufficient protection 

from the elements against impairment of 

the pilot’s vision. 

(4) The openable window specified in 

paragraph (b)(3) of this section need not 

be provided if it is shown that an area 

of the transparent surface will remain 

clear sufficient for at least one pilot to 

land the airplane safely in the event of— 

(i) Any system failure or combination 

of failures which is not extremely 

improbable, in accordance with 

§ 25.1309, under the precipitation 

conditions specified in paragraph (b)(1) 

of this section. 

(ii) An encounter with severe hail, 

birds, or insects. 

* * * * * 

Issued in Washington, DC, on December 

29, 2010. 

K.C. Yanamura, 

Acting Director, Aircraft Certification Service. 

[FR Doc. 2010–33347 Filed 1–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1307; Directorate 

Identifier 2010–NM–049–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–2A12 (CL–601) and 

CL–600–2B16 (CL–601–3A, CL–601– 

3R, and CL–604 Variants) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as 

During flight-testing of a wing anti-ice 

piccolo tube containing a deliberate small 

breach, it was determined that the wing 

leading edge thermal switches were not 

detecting the consequent bleed leak at the 

design threshold. As a result, new 

Airworthiness Limitation tasks, consisting of 

a functional test of the wing leading edge 

thermal switches and an inspection of the 

wing anti-ice duct piccolo tubes, have been 

introduced in order to limit exposure to 

dormant failure of the switches in the event 

of piccolo tube failure, which could 

potentially compromise the structural 

integrity of the wing leading edge and the 

effectiveness of the wing anti-ice system. 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by February 22, 2011. 

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, 


srobinson on DSKHWCL6B1PROD with PROPOSALS
478 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Proposed Rules 

Inc., 400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 

514–855–5000; fax 514–855–7401; 

e-mail 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. 

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–2010–1307; Directorate Identifier 

2010–NM–049–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 

Transport Canada Civil Aviation, 

which is the aviation authority for 

Canada, has issued Canadian 

Airworthiness Directive CF–2009–49R1, 

dated January 21, 2010 (referred to after 

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

condition for the specified products. 

The MCAI states: 

During flight-testing of a wing anti-ice 

piccolo tube containing a deliberate small 

breach, it was determined that the wing 

leading edge thermal switches were not 

detecting the consequent bleed leak at the 

design threshold. As a result, new 

Airworthiness Limitation tasks, consisting of 

a functional test of the wing leading edge 

thermal switches and an inspection of the 

wing anti-ice duct piccolo tubes, have been 

introduced in order to limit exposure to 

dormant failure of the switches in the event 

of piccolo tube failure, which could 

potentially compromise the structural 

integrity of the wing leading edge and the 

effectiveness of the wing anti-ice system. 

This directive mandates the revision of the 

approved maintenance schedule to include 

these new tasks, including phase-in 

schedules. 

This revision clarifies the applicability of 

the directive for CL–600–2A12 aircraft, serial 

numbers 3001 through 3066, and for CL– 

600–2B16 aircraft, serial numbers 5001 

through 5194. The directive is only 

applicable to these aircraft if Bombardier 

Service Bulletin (SB) 601–0590 [Scheduled 

Maintenance Instructions (MSG–3) Derived— 

Qualification] has been incorporated. There 

is no change required to the approved 

maintenance schedule if SB 601–0590 has 

not been incorporated. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier has issued the following 

service information: 

• Challenger 601 Time Limits/ 

Maintenance Checks, PSP 601–5, 

Revision 38, dated June 19, 2009. 

• Challenger 601 Time Limits/ 

Maintenance Checks, PSP 601A–5, 

Revision 34, dated June 19, 2009. 

• Challenger 604 Time Limits/ 

Maintenance Checks, CH 604 TLMC, 

Revision 13, dated August 12, 2009. 

• Challenger 605 Time Limits/ 

Maintenance Checks, CH 605 TLMC, 

Revision 1, dated August 12, 2009. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

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 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 103 products of U.S. 

registry. We also estimate that it would 

take about 1 work-hour per product to 

comply with the 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 

$8,755, or $85 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 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Proposed Rules 479 

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 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: 

Bombardier, Inc.: Docket No. FAA–2010– 

1307; Directorate Identifier 2010–NM– 

049–AD. 

Comments Due Date 

(a) We must receive comments by February 

22, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the airplanes 

identified in paragraphs (c)(1), (c)(2), (c)(3), 

and (c)(4) of this AD; certificated in any 

category. 

(1) Bombardier, Inc. Model CL–600–2A12 

(CL–601) airplanes, serial numbers 3001 

through 3066 inclusive on which Bombardier 

Service Bulletin 601–0590 has been 

accomplished. 

(2) Bombardier, Inc. CL–600–2B16 (CL– 

601–3A and CL–601–3R Variants) airplanes, 

serial numbers 5001 through 5194 inclusive 

on which Bombardier Service Bulletin 601– 

0590 has been accomplished. 

(3) Bombardier, Inc. CL–600–2B16 (CL–604 

Variants) airplanes, serial numbers 5301 

through 5665 inclusive. 

(4) Bombardier, Inc. CL–600–2B16 (CL–604 

Variants) airplanes, serial numbers 5701 and 

subsequent. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (j) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued operational safety of the airplane. 

Subject 

(d) Air Transport Association (ATA) of 

America Codes 30 and 36: Ice and Rain 

Protection and Pneumatic, respectively. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During flight-testing of a wing anti-ice 

piccolo tube containing a deliberate small 

breach, it was determined that the wing 

leading edge thermal switches were not 

detecting the consequent bleed leak at the 

design threshold. As a result, new 

Airworthiness Limitation tasks, consisting of 

a functional test of the wing leading edge 

thermal switches and an inspection of the 

wing anti-ice duct piccolo tubes, have been 

introduced in order to limit exposure to 

dormant failure of the switches in the event 

of piccolo tube failure, which could 

potentially compromise the structural 

integrity of the wing leading edge and the 

effectiveness of the wing anti-ice system. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Within 30 days after the effective date 

of this AD: Revise the Airworthiness 

Limitations Section of the Instructions for 

Continued Airworthiness by incorporating 

the applicable tasks identified in table 1 of 

this AD. 

TABLE 1—AIRWORTHINESS LIMITATIONS TASKS

For Bombardier, Inc. model— Incorporate task(s)— Identified in— 

CL–600–2A12 (CL–601) airplanes, serial numbers 

3001 through 3066 inclusive on which Bombardier Service Bulletin 601–0590 has been accomplished.

30–11–00–101 and 30–11–00–102 ...... Bombardier Challenger 601 Time Limits/Maintenance Checks, PSP 601–5, Revision 38, dated 

June 19, 2009. 

CL–600–2B16 (CL–601–3A and CL–601–3R 

Variants) airplanes, serial numbers 5001 through 

5194 inclusive on which Bombardier Service 

Bulletin 601–0590 has been accomplished.

30–11–00–101 and 30–11–00–102 ...... Bombardier Challenger 601 Time Limits/Maintenance Checks, PSP 601A–5, Revision 34, 

dated June 19, 2009. 

CL–600–2B16 (CL–604 Variants) airplanes, serial 

numbers 5301 through 5665 inclusive.

30–11–00–101 and 36–21–00–101 ...... Bombardier Challenger 604 Time Limits/Maintenance Checks, CH 604 TLMC, Revision 13, 

dated August 12, 2009. 

CL–600–2B16 (CL–604 Variants) airplanes, serial 

numbers 5701 and subsequent.

30–11–00–101 and 36–21–00–101 ...... Bombardier Challenger 605 Time Limits/Maintenance Checks, CH 605 TLMC, Revision 1, 

dated August 12, 2009. 

(h) For all tasks identified in paragraph (g) 

of this AD, the initial compliance times for 

those tasks are within the applicable times 

specified in table 2 of this AD. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
480 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Proposed Rules 

TABLE 2—INITIAL COMPLIANCE TIMES FOR AIRWORTHINESS LIMITATIONS TASKS

Bombardier, Inc. model— Task(s)— Initial compliance time (whichever occurs later)— 

CL–600–2A12 (CL–601) airplanes, serial numbers 3001 through 3066 inclusive; and CL– 

600–2B16 (CL–601–3A and CL–601–3R 

Variants) airplanes, serial numbers 5001 

through 5194 inclusive; on which Bombardier Service Bulletin 601–0590 has been 

accomplished.

30–11–00–101 ........... Prior to the accumulation of 4,800 total flight 

hours; or within 4,800 flight hours after accomplishing Task 30–11–06–204 in Section 

5–20–15 of the applicable Time Limits/ 

Maintenance Checks manual; whichever 

occurs later.

Within 240 flight hours 

after the effective 

date of this AD. 

CL–600–2A12 (CL–601) airplanes, serial numbers 3001 through 3066 inclusive; and CL– 

600–2B16 (CL–601–3A and CL–601–3R 

Variants) airplanes, serial numbers 5001 

through 5194 inclusive; on which Bombardier Service Bulletin 601–0590 has been 

accomplished.

30–11–00–102 ........... Prior to the accumulation of 4,800 total flight 

hours; or within 4,800 flight hours after accomplishing Task 30–13–00–205 in Section 

5–20–15 of the applicable Time Limits/ 

Maintenance Checks manual; whichever 

occurs later.

Within 240 flight hours 

after the effective 

date of this AD. 

CL–600–2B16 (CL–604 Variants) airplanes, 

serial numbers 5301 through 5665 inclusive.

30–11–00–101 and 

36–21–00–101.

Prior to the accumulation of 6,400 total flight 

hours; except for airplanes having 6,400 

total flight hours or more as of the effective 

date of this AD on which the task has not 

been accomplished: Prior to the next 

scheduled 6,400 flight hour task inspection 

or prior to the next scheduled accomplishment of Task 57–10–00–208 in the applicable Time Limits/Maintenance Checks manual, whichever occurs first.

Within 320 flight hours 

after the effective 

date of this AD. 

CL–600–2B16 (CL–604 Variants) airplanes, 

serial numbers 5701 and subsequent.

30–11–00–101 and 

36–21–00–101.

Prior to the accumulation of 6,400 total flight 

hours.

Within 320 flight hours 

after the effective 

date of this AD. 

(i) After accomplishing the actions 

required by paragraph (g) of this AD, no 

alternative tasks or task intervals may be 

used unless the tasks or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (j)(1) of 

this AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office, ANE–170, FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information 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 

on any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards 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 FAAapproved 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. 

(3) Reporting Requirements: A Federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave., SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(k) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–49R1, dated January 21, 

2010, and the service information specified 

in Table 1 of this AD for related information. 

Issued in Renton, Washington, on 

December 27, 2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–33329 Filed 1–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1306; Directorate 

Identifier 2010–NM–112–AD] 

RIN 2120–AA64 

Airworthiness Directives; DassaultAviation Model FALCON 7X Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

A design review has revealed a potential 

dormant failure of the Ram Air Turbine 

(RAT) heating system. If this failure occurs, 

it could lead to the freezing of the RAT 

mechanism and the consequent nondeployment of the RAT when needed. 

* * * * * 

Non-deployment of the RAT could 

result in insufficient electrical power to 

operate the fly-by-wire system, and 


srobinson on DSKHWCL6B1PROD with PROPOSALS