Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Proposed Rules 6581 

(1) The associated interval for any new task 

is to be counted from April 9, 2007. 

(2) The associated interval for any revised 

task is to be counted from the previous 

performance of the task. 

New Requirements of This AD 

Revise the Maintenance Program 

(g) Unless already done, within 90 days of 

the effective date of this AD: Revise the 

maintenance program which ensures the 

continuing airworthiness of each operated 

airplane by incorporating Airbus A330 ALS, 

Part 3—Certification Maintenance 

Requirements, Revision 03, dated July 29, 

2010. At the times specified in the Airbus 

A330 ALS, Part 3—Certification Maintenance 

Requirements, Revision 03, dated July 29, 

2010, comply with all applicable 

maintenance requirements and associated 

airworthiness limitations included in Airbus 

A330 ALS, Part 3—Certification Maintenance 

Requirements, Revision 03, dated July 29, 

2010, except as provided by paragraphs (h) 

and (i) of this AD. Doing this revision 

terminates the requirements of paragraph (f) 

of this AD for that airplane only. 

Exceptions to the CMR Tasks 

(h) At the latest of the times specified in 

paragraph (h)(1), (h)(2), or (h)(3) of this AD: 

Do the first accomplishment of CMR Task 

213100–00001–2–C of Airbus A330 ALS, Part 

3—Certification Maintenance Requirements, 

Revision 03, dated July 29, 2010. 

(1) Before the accumulation of 48,000 total 

flight hours. 

(2) Within 48,000 flight hours after the 

most recent accomplishment of Maintenance 

Review Board Report (MRBR) Task 21.31.00/ 

05. 

(3) Within three months after the effective 

date of this AD. 

(i) At the latest of the times specified in 

paragraph (i)(1), (i)(2), or (i)(3) of this AD: Do 

the first accomplishment of CMR Tasks 

242000–00005–1–C, 243000–00001–1–C, and 

243000–00002–1–C of Airbus A330 ALS, Part 

3—Certification Maintenance Requirements, 

Revision 03, dated July 29, 2010. 

(1) Before the accumulation of 12,000 total 

flight hours. 

(2) Within 12,000 flight hours after the 

most recent accomplishment of MRBR Task 

24.20.00/17, 24.30.00/04, or 24.30.00/05 

respectively. 

(3) Within three months after the effective 

date of this AD. 

No Alternative Inspections or Intervals 

(j) After accomplishing the action required 

by paragraph (g) of this AD, no alternative 

inspections or inspection intervals may be 

used, unless the inspections or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (k)(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 

(k) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, ANM–116, 

International Branch, Transport Airplane 

Directorate, 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: Vladimir 

Ulyanov, Aerospace Engineer, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, 1601 Lind Avenue SW., 

Renton, Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 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 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. 

Related Information 

(l) Refer to EASA Airworthiness Directives 

2006–0225, dated July 21, 2006, and 2010– 

0264, dated December 20, 2010; Airbus A330 

Certification Maintenance Requirements, 

Document 955.2074/93, Issue 19, dated 

March 22, 2006; and Airbus A330 ALS, Part 

3—Certification Maintenance Requirements, 

Revision 03, dated July 29, 2010; for related 

information. 

Issued in Renton, Washington, on January 

28, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–2611 Filed 2–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0037; Directorate 

Identifier 2010–NM–273–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

Series Airplanes, and Model C4–605R 

Variant F Airplanes (Collectively Called 

A300–600 Series 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: 

[T]he FAA has published SFAR 88 (Special 

Federal Aviation Regulation 88). 

In their letters referenced 04/00/02/07/01– 

L296, dated March 4th, 2002, and 04/00/02/ 

07/03–L024, dated February 3rd, 2003, the 

JAA [Joint Aviation Authorities] 

recommended the application of a similar 

regulation to the National Aviation 

Authorities (NAA). 

Under this regulation, all holders of type 

certificates for passenger transport aircraft 

* * * are required to conduct a design 

review against explosion risks. 

During improvement of the protection of 

fuel pump wiring against short-circuit by 

accomplishment of Airbus Service Bulletin 

(SB) A300–24–6094, a study led by the 

manufacturer concluded that the harness, 

installed through the wing panel needed to 

be protected to prevent possible damage in 

case of chafing which could potentially lead 

to short-circuit [and intermittent function or 

loss of the inner tank fuel pump. Loss of both 

inner tank fuel pumps could result in 

inability to use the remaining fuel supply in 

the inner tank. A short-circuit could also 

result in an ignition source in a flammable 

leakage zone]. 

* * * * * 

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 March 24, 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 W12–40, 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 Airbus SAS— 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; e-mail: 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
6582 Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Proposed Rules 

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: 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. 

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–2011–0037; Directorate Identifier 

2010–NM–273–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0225, 

dated November 5, 2010 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

[T]he FAA has published SFAR 88 (Special 

Federal Aviation Regulation 88). 

In their letters referenced 04/00/02/07/01– 

L296, dated March 4th, 2002, and 04/00/02/ 

07/03–L024, dated February 3rd, 2003, the 

JAA [Joint Aviation Authorities] 

recommended the application of a similar 

regulation to the National Aviation 

Authorities (NAA). 

Under this regulation, all holders of type 

certificates for passenger transport aircraft 

with either a passenger capacity of 30 or 

more, or a payload capacity of 3,402 kg 

(7,500 lb) or more, which have received their 

certification since January 1st, 1958, are 

required to conduct a design review against 

explosion risks. 

During improvement of the protection of 

fuel pump wiring against short-circuit by 

accomplishment of Airbus Service Bulletin 

(SB) A300–24–6094, a study led by the 

manufacturer concluded that the harness, 

installed through the wing panel needed to 

be protected to prevent possible damage in 

case of chafing which could potentially lead 

to short-circuit [and intermittent function or 

loss of the inner tank fuel pump. Loss of both 

inner tank fuel pumps could result in 

inability to use the remaining fuel supply in 

the inner tank. A short-circuit could also 

result in an ignition source in a flammable 

leakage zone]. 

For the reasons stated above, this [EASA] 

AD requires the replacement of bushes in the 

hydraulic reservoir panel. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’ 

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 

requires certain type design (i.e., type 

certificate (TC) and supplemental type 

certificate (STC)) holders to substantiate 

that their fuel tank systems can prevent 

ignition sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the rule, we intended to adopt 

airworthiness directives to mandate any 

changes found necessary to address 

unsafe conditions identified as a result 

of these reviews. 

In evaluating these design reviews, we 

have established four criteria intended 

to define the unsafe conditions 

associated with fuel tank systems that 

require corrective actions. The 

percentage of operating time during 

which fuel tanks are exposed to 

flammable conditions is one of these 

criteria. The other three criteria address 

the failure types under evaluation: 

single failures, single failures in 

combination with a latent condition(s), 

and in-service failure experience. For all 

four criteria, the evaluations included 

consideration of previous actions taken 

that may mitigate the need for further 

action. 

The Joint Aviation Authorities (JAA) 

has issued a regulation that is similar to 

SFAR 88. (The JAA is an associated 

body of the European Civil Aviation 

Conference (ECAC) representing the 

civil aviation regulatory authorities of a 

number of European States who have 

agreed to co-operate in developing and 

implementing common safety regulatory 

standards and procedures.) Under this 

regulation, the JAA stated that all 

members of the ECAC that hold type 

certificates for transport category 

airplanes are required to conduct a 

design review against explosion risks. 

We have determined that the actions 

identified in this AD are necessary to 

reduce the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A300–24–6102, Revision 01, 

dated September 24, 2010. 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. 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
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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 120 products of U.S. 

registry. We also estimate that it would 

take about 13 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $266 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these costs. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$164,520, or $1,371 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 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: 

Airbus: Docket No. FAA–2011–0037; 

Directorate Identifier 2010–NM–273–AD. 

Comments Due Date 

(a) We must receive comments by March 

24, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Airbus Model 

A300 B4–601, B4–603, B4–620, B4–622, B4– 

605R, B4–622R, F4–605R, F4–622R, and C4– 

605R Variant F airplanes, certificated in any 

category, all certified models, all serial 

numbers, except airplanes on which Airbus 

Service Bulletin A300–24–6102 (Airbus 

Modification 13381) has been embodied. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 24: Electrical Power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

[T]he FAA has published SFAR 88 (Special 

Federal Aviation Regulation 88). 

In their letters referenced 04/00/02/07/01– 

L296, dated March 4th, 2002, and 04/00/02/ 

07/03–L024, dated February 3rd, 2003, the 

JAA [Joint Aviation Authorities] 

recommended the application of a similar 

regulation to the National Aviation 

Authorities (NAA). 

Under this regulation, all holders of type 

certificates for passenger transport aircraft 

* * * are required to conduct a design 

review against explosion risks. 

During improvement of the protection of 

fuel pump wiring against short-circuit by 

accomplishment of Airbus Service Bulletin 

(SB) A300–24–6094, a study led by the 

manufacturer concluded that the harness, 

installed through the wing panel needed to 

be protected to prevent possible damage in 

case of chafing which could potentially lead 

to short-circuit [and intermittent function or 

loss of the inner tank fuel pump. Loss of both 

inner tank fuel pumps could result in 

inability to use the remaining fuel supply in 

the inner tank. A short-circuit could also 

result in an ignition source in a flammable 

leakage zone]. 

* * * * * 

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 months after the effective 

date of this AD, install Teflon bushes in the 

hydraulic reservoir panel at the lower lefthand side in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–24–6102, 

Revision 01, dated September 24, 2010. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Actions done before the effective date 

of this AD in accordance with Airbus 

Mandatory Service Bulletin A300–24–6102, 

dated August 13, 2009, are acceptable for 

compliance with the corresponding 

requirements of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) 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. 

Send information to ATTN: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
6584 Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Proposed Rules 

Washington 98057–3356; telephone (425) 

227–2125; fax (425) 227–1149. Information 

may be e-mailed to: 9-ANM-116-AMOCREQUESTS@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. 

Related Information 

(j) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2010–0225, 

dated November 5, 2010; and Airbus 

Mandatory Service Bulletin A300–24–6102, 

Revision 01, dated September 24, 2010; for 

related information. 

Issued in Renton, Washington, on January 

31, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–2612 Filed 2–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0036; Directorate 

Identifier 2010–NM–230–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8–400 Series 

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: 

Bombardier Aerospace has completed a 

system safety review of the aeroplanes fuel 

system against fuel tank safety standards 

introduced in Chapter 525 of the 

Airworthiness Manual through Notice of 

Proposed Amendment (NPA) 2002–043 

[which corresponds with the FAA’s Special 

Federal Aviation Regulation (SFAR) 88]. The 

identified non-compliances were then 

assessed using Transport Canada Policy 

Letter No. 525–001, to determine if 

mandatory corrective action is required. 

The assessment showed that a number of 

modifications to the fuel system are required 

to mitigate unsafe conditions that could 

result in potential ignition source within the 

fuel 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 March 24, 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 W12–40, 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; e-mail 

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: 

James Delisio, Aerospace Engineer, 

Propulsion and Services Branch, ANE– 

173, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7321; 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–2011–0036; Directorate Identifier 

2010–NM–230–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 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2010–31, 

dated September 3, 2010 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

Bombardier Aerospace has completed a 

system safety review of the aeroplanes fuel 

system against fuel tank safety standards 

introduced in Chapter 525 of the 

Airworthiness Manual through Notice of 

Proposed Amendment (NPA) 2002–043 

[which corresponds with the FAA’s Special 

Federal Aviation Regulation (SFAR) 88]. The 

identified non-compliances were then 

assessed using Transport Canada Policy 

Letter No. 525–001, to determine if 

mandatory corrective action is required. 

The assessment showed that a number of 

modifications to the fuel system are required 

to mitigate unsafe conditions that could 

result in potential ignition source within the 

fuel system. 

The Bombardier modifications 

include: 

• Modsum 4–126330, ‘‘Fuel Tank 

System Design Left and Right Side 

(SFAR 88) Retrofit.’’ The retrofit 

includes replacing certain fittings, 

couplings, o-rings, gaskets, fuel adapter, 

and other related components with new, 

improved parts; applying alodine 1132 

to certain areas of a wing rib and a wing 

spar; and replacing a certain doubler on 

the front wing spar with a new, 

improved doubler. 

• Modsum 4–126366, ‘‘Fuel Tank 

System and Fuel Indication—Wiring 

Identification, Segregation and 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1