18960 Federal Register / Vol. 76, No. 66 / Wednesday, April 6, 2011 / Proposed Rules 

(2) Do a detailed inspection for cracks of 

the joint extrusion of the upper and lower 

transcowl assembly on the left and right 

engines at the location of the joint piece. If 

no cracks are found, close the cowlings on 

the left and right engines. 

(3) If any crack is found on one or more 

transcowl assemblies during the inspection 

required by paragraph (h)(2) of this AD, 

before further flight, repair and reinforce the 

cracked part(s) in accordance with paragraph 

(i)(1) of this AD. 

Note 1: Procedure-Part 3 of Task 05–51– 

27–210–801 of Part 2, Volume 1, of the 

Bombardier CRJ Series Regional Jet AMM, 

CSP B–001, Revision 34, dated November 20, 

2010, gives guidance for opening and closing 

the cowling on the left and right engines. 

(i) For transcowl assemblies identified in 

paragraph (g)(2) of this AD: Except as 

required by paragraph (h) of this AD, within 

5,000 flight hours or 24 months after the 

effective date of this AD, whichever comes 

first, do a detailed inspection for cracking on 

each transcowl assembly, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 670BA–78–008, 

Revision B, dated December 22, 2010; or 

Bombardier Service Bulletin 670SH–78–029, 

Revision C, dated November 10, 2010. 

Accomplishment of the actions specified in 

paragraph (i)(1) or (i)(2) of this AD for all 

transcowl assemblies identified in paragraph 

(g)(2) of this AD terminates the requirements 

of paragraph (h) of this AD. 

(1) If any cracking of the joint extrusion is 

found, before further flight, repair and 

reinforce the joint extrusion on each 

transcowl assembly, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–78–008, Revision B, 

dated December 22, 2010; or Bombardier 

Service Bulletin 670SH–78–029, Revision C, 

dated November 10, 2010. 

(2) If no cracking is found, before further 

flight, reinforce the joint extrusion on each 

transcowl assembly, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–78–008, Revision B, 

dated December 22, 2010; or Bombardier 

Service Bulletin 670SH–78–029, Revision C, 

dated November 10, 2010. 

Credit for Actions Accomplished in 

Accordance with Previous Service 

Information 

(j) Inspections, repairs, and reinforcement 

of the joint extrusion on each transcowl is 

also acceptable for compliance with the 

corresponding requirements of paragraph (i) 

of this AD if done before the effective date 

of this AD in accordance with the service 

information listed in table 1 of this AD. 

TABLE 1—SERVICE INFORMATION

Document Revision Date 

Bombardier Service Bulletin 670BA–78–008 ....................................................... Original .................................................. September 19, 2008. 

Bombardier Service Bulletin 670BA–78–008 ....................................................... A ............................................................ July 10, 2009. 

Bombardier Service Bulletin 670SH–78–029 ....................................................... Original .................................................. July 3, 2008. 

Bombardier Service Bulletin 670SH–78–029 ....................................................... A ............................................................ June 30, 2009. 

Bombardier Service Bulletin 670SH–78–029 ....................................................... B ............................................................ November 25, 2009. 

Parts Installation 

(k) As of the effective date of this AD, no 

replacement or spare transcowl assembly 

having P/N CN624–2001–XXX or KCN624– 

2001–X (XXX and X mean various dash 

numbers), with S/N SB0964 or lower, may be 

installed on any airplane, except for a 

transcowl assembly on which any repair 

listed in paragraph 1.D. of Bombardier 

Service Bulletin 670BA–78–008, Revision B, 

dated December 22, 2010, or paragraph 1.A. 

of Bombardier Service Bulletin 670SH–78– 

029, Revision C, dated November 10, 2010, 

has been done; and except for a transcowl 

that has been inspected as specified in 

paragraph (i) of this AD and all applicable 

actions specified in paragraph (i)(1) or (i)(2) 

of this AD, as applicable, have been done. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(l) 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, 1600 Stewart Avenue, Suite 40, 

Westbury, N.Y. 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 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. 

Related Information 

(m) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–33, dated July 28, 2009; 

Bombardier Service Bulletin 670BA–78–008, 

Revision B, dated December 22, 2010; and 

Bombardier Service Bulletin 670SH–78–029, 

Revision C, dated November 10, 2010; for 

related information. 

Issued in Renton, Washington, on March 

24, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–8197 Filed 4–5–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0264; Directorate 

Identifier 2009–NM–244–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 that would 

supersede an existing AD. 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). * * * 

Under this regulation, all holders of type 

certificates for passenger transport aeroplanes 

* * * are required to conduct a design 

review against explosion risks. The 

replacement of some types of P-clips and 


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improvement of the electrical bonding of the 

equipment in the fuel tanks [were] are 

rendered mandatory * * *. 

* * * * * 

Subsequently, an internal review * * * led 

* * * to * * * an additional check [for blue 

coat] of the bonding points in the centre tank. 

* * * 

More recently, another internal review 

[introduced] additional work [installing 

bonding points] for aeroplanes under 

Configuration 03 * * * and additional work 

[bonding the fuel jettison system—blanking 

plates] on the wing tanks for aeroplanes 

under Configuration 07 * * *. 

The unsafe condition is damage to 

wiring in the wing, center, and trim fuel 

tanks, due to failed P-clips used for 

retaining the wiring and pipes, which 

could result in a possible fuel ignition 

source in the wing, center, or trim fuel 

tanks. 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 May 23, 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 

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–2011–0264; Directorate Identifier 

2009–NM–244–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 January 18, 2008, we issued AD 

2008–03–04, Amendment 39–15353 (73 

FR 5731, January 31, 2008). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2008–03–04, 

internal reviews by the manufacturer 

have shown that additional work is 

necessary on the center and wing fuel 

tanks. The European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community, has issued EASA 

Airworthiness Directive 2010–0074, 

dated April 16, 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 04 March 2002, and 04/00/02/07/03– 

L024, dated 03 February 2003, the JAA 

recommended the application of a similar 

regulation to the National Aviation 

Authorities (NAA). 

Under this regulation, all holders of type 

certificates for passenger transport aeroplanes 

with either a passenger capacity of 30 or 

more, or a payload capacity of 3,402 kg 

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

certification since 01 January 1958, are 

required to conduct a design review against 

explosion risks. The replacement of some 

types of P-clips and improvement of the 

electrical bonding of the equipment in the 

fuel tasks are rendered mandatory by this 

AD. 

Initially, EASA AD 2006–0325, which 

addressed the same unsafe condition, also 

applied to A300–600 aeroplanes. Airbus 

subsequently introduced additional work at 

Revision 1 of SB A300–28–6064 [dated April 

3, 2007] applicable to A300–600 aeroplanes. 

As a result, EASA AD 2006–0325 was revised 

to remove A300–600 aeroplanes from the 

applicability, and concurrently EASA AD 

2007–0233 was issued, applicable to A300– 

600 aeroplanes. Unfortunately, the 

‘Applicability’ section of EASA AD 2007– 

0233 was not correctly defined, erroneously 

deleting one modification in the combination 

that would exclude aeroplanes from having 

to comply. Consequently, the AD 2007–0283 

was issued, requiring the same actions as AD 

2007–0233, which was superseded, but 

expanded the group of aeroplanes to which 

AD 2007–0283 applied [FAA AD 2008–03–04 

corresponds with EASA AD 2007–0283]. 

Subsequently, an internal review of Airbus 

SB A300–28–6064 led the manufacturer to 

correct the figures of the SB. In particular, an 

additional check [for blue coat] of the 

bonding points in the centre tank was 

introduced in Revision 03 of Airbus SB 

A300–28–6064 [dated December 15, 2008], 

prompting EASA to issue AD 2009–0143. 

More recently, another internal review of 

Airbus SB A300–28–6064 again resulted in 

corrected figures in the SB. Additional work 

on the center tank [installing bonding points] 

for aeroplanes under Configuration 03 (as 

defined in the SB [Service Bulletin A300–28– 

6064, Revision 04, dated August 24, 2009]) 

and additional work [bonding the fuel 

jettison system—blanking plates] on the wing 

tanks for aeroplanes under Configuration 07 

have been introduced in Revision 04 of 

Airbus SB A300–28–6064 [dated August 24, 

2009]. 

For the reason described above, this new 

AD retains the requirements of EASA AD 

2009–0143, which is superseded, and 

requires the additional work introduced in 

Revision 04 of Airbus SB A300–28–6064 

[dated August 24, 2009]. 

The unsafe condition is damage to 

wiring in the wing, center, and trim fuel 

tanks, due to failed P-clips used for 

retaining the wiring and pipes, which 

could result in a possible fuel ignition 

source in the wing, center, or trim fuel 

tanks. The required actions also include 

checking the electrical bonding points 

of certain equipment in the center fuel 

tank for the presence of a blue coat and 

doing related investigative and 

corrective actions if necessary. The 

related investigative action is to 

measure the electrical resistance 

between the equipment and structure, if 

a blue coat is not present. The corrective 

action is to electrically bond the 


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equipment, if the measured resistance is 

greater than 10 milliohms. You may 

obtain further information by examining 

the MCAI in the AD docket. 

We have also revised paragraphs (f)(4) 

and (f)(5) of AD 2008–03–04 (reidentified as paragraphs (g)(6) and (g)(7) 

in this NPRM) by replacing the term 

‘‘service bulletin’’ with the full service 

bulletin citation. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletins A300–28–6064, Revision 03, 

dated December 15, 2008; and Revision 

04, dated August 24, 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 125 products of U.S. 

registry. 

The actions that are required by AD 

2008–03–04 and retained in this 

proposed AD take about 632 work-hours 

per product, at an average labor rate of 

$85 per work hour. Required parts cost 

about $6,870 per product. Based on 

these figures, the estimated cost of the 

currently required actions is $60,590 per 

product. 

We estimate that it would take about 

9 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Required parts 

would cost about $100 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 $108,125, or $865 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 

removing Amendment 39–15353 (73 FR 

5731, January 31, 2008) and adding the 

following new AD: 

Airbus: Docket No. FAA–2011–0264; 

Directorate Identifier 2009–NM–244–AD. 

Comments Due Date 

(a) We must receive comments by May 23, 

2011. 

Affected ADs 

(b) This AD supersedes AD 2008–03–04, 

Amendment 39–15353. 

Applicability 

(c) This AD applies to the airplanes 

identified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) Airbus Model A300 B4–601, B4–603, 

B4–620, and B4–622 airplanes (without trim 

tank), all serial numbers, certificated in any 

category, except airplanes on which Airbus 

Modifications 12226, 12365, 12490, and 

12308 have been incorporated in production, 

or Airbus Mandatory Service Bulletin A300– 

28–6064, Revision 04, dated August 24, 2009; 

and Airbus Service Bulletin A300–28–6068, 

dated July 20, 2005; have been performed in 

service. 

(2) Airbus Model A300 B4–605R, B4–622R, 

F4–605R, and F4–622R airplanes and A300 

C4–605R Variant F airplanes (fitted with a 

trim tank), all serial numbers, certificated in 

any category, except airplanes on which 

Airbus Modifications 12226, 12365, 12490, 

12308, 12294, and 12476 have been 

incorporated in production, or on which the 

service bulletins listed in paragraphs (c)(2)(i), 

(c)(2)(ii), and (c)(2)(iii) of this AD have been 

performed in service. 

(i) Airbus Mandatory Service Bulletin 

A300–28–6064, Revision 03, dated December 

15, 2008. 

(ii) Airbus Service Bulletin A300–28–6068, 

dated July 20, 2005. 

(iii) Airbus Service Bulletin A300–28– 

6077, dated July 25, 2005; or A300–28–6077, 

Revision 01, dated October 26, 2006. 


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Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

[T]he FAA has published SFAR 88 (Special 

Federal Aviation Regulation 88). * * * 

Under this regulation, all holders of type 

certificates for passenger transport aeroplanes 

* * * are required to conduct a design 

review against explosion risks. The 

replacement of some types of P-clips and 

improvement of the electrical bonding of the 

equipment in the fuel tanks [were] are 

rendered mandatory * * *. 

* * * * * 

Subsequently, an internal review * * * led 

* * * to * * * an additional check [for blue 

coat] of the bonding points in the centre tank. 

* * * 

More recently, another internal review 

[introduced] additional work [installing 

bonding points] for aeroplanes under 

Configuration 03 * * * and additional work 

[bonding the fuel jettison system—blanking 

plates] on the wing tanks for aeroplanes 

under Configuration 07 * * *. 

The unsafe condition is damage to wiring 

in the wing, center, and trim fuel tanks, due 

to failed P-clips used for retaining the wiring 

and pipes, which could result in a possible 

fuel ignition source in the wing, center, or 

trim fuel tanks. 

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. 

Restatement of Requirements of AD 2008– 

03–04 With Revised Service Information 

Actions and Compliance 

(g) For airplanes identified in paragraphs 

(g)(1) and (g)(2) of this AD: Within 40 months 

after March 6, 2008 (the effective date of AD 

2008–03–04), unless already done, do the 

applicable actions required by paragraphs 

(g)(3), (g)(4), and (g)(5) of this AD. 

(1) Airbus Model A300 B4–600 series 

airplanes (without trim tank), all serial 

numbers, except airplanes on which Airbus 

Modifications 12226, 12365, 12490, and 

12308 have been incorporated in production, 

or Airbus Service Bulletins A300–28–6064, 

Revision 01, dated April 3, 2007; and A300– 

28–6068, dated July 20, 2005; have been 

performed in service. 

(2) Airbus Model A300 B4–600R, A300 C4– 

600R, and A300 F4–600R series airplanes 

(fitted with a trim tank), all serial numbers, 

except airplanes on which Airbus 

Modifications 12226, 12365, 12490, 12308, 

12294, and 12476 have been incorporated in 

production, or on which the service bulletins 

listed in paragraphs (g)(2)(i), (g)(2)(ii), and 

(g)(2)(iii) of this AD have been performed in 

service. 

(i) Airbus Service Bulletin A300–28–6064, 

Revision 01, dated April 3, 2007. 

(ii) Airbus Service Bulletin A300–28–6068, 

dated July 20, 2005. 

(iii) Airbus Service Bulletin A300–28– 

6077, dated July 25, 2005; or A300–28–6077, 

Revision 01, dated October 26, 2006. 

(3) Remove NSA5516–XXND or NSA5516– 

XXNJ type P-clips, used in the wing and 

center fuel tanks to retain wiring and pipes, 

and replace them by NSA5516–XXNF type Pclips in accordance with the instructions of 

Airbus Service Bulletin A300–28–6068, 

dated July 20, 2005. 

(4) Check the electrical bonding points in 

the center tank and do all applicable related 

investigative and corrective actions, and 

install additional bonding leads and 

electrical bonding points in the wing and 

center fuel tanks in accordance with the 

instructions of Airbus Service Bulletin A300– 

28–6064, Revision 01, dated April 3, 2007; 

Airbus Mandatory Service Bulletin A300–28– 

6064, Revision 02, dated March 10, 2008; 

Airbus Mandatory Service Bulletin A300–28– 

6064, Revision 03, dated December 15, 2008; 

or Airbus Mandatory Service Bulletin A300– 

28–6064, Revision 04, dated August 24, 2009. 

Do all applicable related investigative and 

corrective actions before further flight. As of 

the effective date of this AD, only use Airbus 

Mandatory Service Bulletin A300–28–6064, 

Revision 04, dated August 24, 2009. 

(5) For airplanes fitted with a trim tank, in 

addition to the actions defined in paragraphs 

(g)(3) and (g)(4) of this AD, install bonding 

leads and electrical bonding points in the 

trim tanks, in accordance with the 

instructions of Airbus Service Bulletin A300– 

28–6077, Revision 01, dated October 26, 

2006. 

(6) Actions done before March 6, 2008, in 

accordance with Airbus Service Bulletin 

A300–28–6064, dated July 28, 2005, for 

aircraft under configuration 05, as defined 

Airbus Service Bulletin A300–28–6064, 

dated July 28, 2005, are considered 

acceptable for compliance with the 

requirements of paragraph (g)(4) of this AD. 

(7) Actions done before March 6, 2008, in 

accordance with Airbus Service Bulletin 

A300–28–6077, dated July 25, 2005, for 

aircraft under configuration 05, as defined in 

Airbus Service Bulletin A300–28–6077, 

dated July 25, 2005, are considered 

acceptable for compliance with the 

requirements of paragraph (g)(5) of this AD. 

New Requirments of This AD 

Additional Actions 

(h) Within 8 months after the effective date 

of this AD, do the applicable actions required 

by paragraphs (h)(1), (h)(2), and (h)(3) of this 

AD. 

(1) For airplanes that have been modified 

before the effective date of this AD in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

28–6064, dated July 28, 2005; Revision 01, 

dated April 3, 2007; or Airbus Mandatory 

Service Bulletin A300–28–6064, Revision 02, 

dated March 10, 2008: Do the additional 

work on the center tank specified in Airbus 

Mandatory Service Bulletin A300–28–6064, 

Revision 03, dated December 15, 2008, (i.e., 

a check for blue coat at additional bonding 

points and all applicable related investigative 

and corrective actions), in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–28–6064, 

Revision 03, dated December 15, 2008; or 

Revision 04, dated August 24, 2009. Do all 

applicable related investigative and 

corrective actions before further flight. 

(2) For configuration 03 airplanes, as 

defined in Airbus Mandatory Service 

Bulletin A300–28–6064, Revision 04, dated 

August 24, 2009, that have been modified 

before the effective date of this AD in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

28–6064, Revision 01, dated April 3, 2007; or 

Airbus Mandatory Service Bulletin A300–28– 

6064, Revision 02, dated March 10, 2008, or 

Revision 03, dated December 15, 2008: Do 

the additional work on the center tank (i.e., 

install bonding points), in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–28–6064, 

Revision 04, dated August 24, 2009. 

(3) For configuration 07 airplanes, as 

defined in Airbus Mandatory Service 

Bulletin A300–28–6064, Revision 04, dated 

August 24, 2009, that have been modified 

before the effective date of this AD in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

28–6064, dated July 28, 2005; Revision 01, 

dated April 3, 2007; or Airbus Mandatory 

Service Bulletin A300–28–6064, Revision 02, 

dated March 10, 2008, or Revision 03, dated 

December 15, 2008: Do the additional work 

on the wing tanks (i.e., bond the fuel jettison 

system—blanking plates), in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–28–6064, 

Revision 04, dated August 24, 2009. 

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, 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, 

Washington 98057–3356; telephone (425) 

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

approved previously in accordance with AD 

2008–03–04 are approved as AMOCs for the 

corresponding provisions of 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. 


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18964 Federal Register / Vol. 76, No. 66 / Wednesday, April 6, 2011 / Proposed Rules 

Related Information 

(j) Refer to MCAI EASA Airworthiness 

Directive 2010–0074, dated April 16, 2010, 

and the service information listed in Table 1 

of this AD, for related information. 

TABLE 1—SERVICE INFORMATION

Airbus service information Revision level Date 

Airbus Mandatory Service Bulletin A300–28–6064 ............................................. 03 .......................................................... December 15, 2008. 

Airbus Mandatory Service Bulletin A300–28–6064 ............................................. 04 .......................................................... August 24, 2009. 

Airbus Service Bulletin A300–28–6068 ................................................................ Original .................................................. July 20, 2005. 

Airbus Service Bulletin A300–28–6077 ................................................................ 01 .......................................................... October 26, 2006. 

Issued in Renton, Washington, on March 

23, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–8198 Filed 4–5–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0326; Directorate 

Identifier 2011–CE–006–AD] 

RIN 2120–AA64 

Airworthiness Directives; Costruzioni 

Aeronautiche Tecnam srl Model 

P2006T Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (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 Landing Gear retraction/extension 

ground checks performed on the P2006T, a 

loose Seeger ring was found on the nose 

landing gear hydraulic actuator cap. 

The manufacturer has identified the root 

cause of this discrepancy in a design 

deficiency of the hydraulic actuator caps. 

This condition, if not corrected, could 

determine uncommanded and improper 

extension of the nose or main landing gear. 

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 May 23, 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 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Costruzioni 

Aeronautiche TECNAM Airworthiness 

Office, Via Maiorise—81043 Capua (CE) 

Italy; telephone: +39 0823 620134; fax: 

+39 0823 622899; e-mail: 

m.oliva@tecnam.com, 

p.violetti@tecnam.com; Internet: http:// 

www.tecnam.com. You may review 

copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call 816–329–4148. 

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 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Albert Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4119; fax: (816) 329–4090. 

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–2011–0326; Directorate Identifier 

2011–CE–006–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD No.: 

2011–0042, dated March 11, 2011 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

During Landing Gear retraction/extension 

ground checks performed on the P2006T, a 

loose Seeger ring was found on the nose 

landing gear hydraulic actuator cap. 

The manufacturer has identified the root 

cause of this discrepancy in a design 

deficiency of the hydraulic actuator caps. 

This condition, if not corrected, could 

determine uncommanded and improper 

extension of the nose or main landing gear. 

To prevent this condition, this AD requires 

modifying each nose and main landing gear 

hydraulic actuator by installing security 

rings. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Costruzioni Aeronautiche Tecnam has 

issued Service Bulletin No. SB 036–CS, 

1st Edition, Rev 1, dated December 15, 

2010. The actions described in this 


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