Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations 68185 

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: Tim Dulin, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2141; 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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(n) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2009– 

0141, dated July 2, 2009, and the service 

information identified in Table 2 of this AD, 

for related information. 

TABLE 2—AIRBUS SERVICE INFORMATION

Document Revision/issue Date 

Airbus All Operators Telex A320–55A1038 ............................................................................... Revision 01 ................. June 10, 2009. 

Airbus All Operators Telex A320–55A1038 ............................................................................... Revision 02 ................. September 28, 2009. 

Airbus Technical Disposition TD/K4/S2/27086/2009 ................................................................. Issue E ....................... September 17, 2009. 

Material Incorporated by Reference 

(o) You must use the service information 

contained in Table 3 of this AD to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

TABLE 3—MATERIAL INCORPORATED BY REFERENCE

Document Revision/issue Date 

Airbus All Operators Telex A320–55A1038* ............................................................................. Revision 01 ................. June 10, 2009. 

Airbus All Operators Telex A320–55A1038* ............................................................................. Revision 02 ................. September 28, 2009. 

Airbus Technical Disposition TD/K4/S2/27086/2009 ................................................................. Issue E ....................... September 17, 2009. 

(* The first page of these documents contain the document number, revision level, and date; no other pages contain this information.) 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 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. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/ibr_

locations.html. 

Issued in Renton, Washington, on October 

26, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–27614 Filed 11–4–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0640; Directorate 

Identifier 2009–NM–142–AD; Amendment 

39–16494; AD 2010–23–05] 

RIN 2120–AA64 

Airworthiness Directives; EADS CASA 

(Type Certificate Previously Held by 

Construcciones Aeronauticas, S.A.) 

Model CN–235, CN–235–100, CN–235– 

200, and CN–235–300 Airplanes, and 

Model C–295 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. This 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: 

Prompted by [an] accident * * *the FAA 

published SFAR 88 (Special Federal Aviation 

Regulation 88) * * *. 

* * * * * 

Fuel Airworthiness Limitations arising 

from the required systems safety analysis are 

items that have been shown to have failure 

mode(s) associated with an ‘unsafe condition’ 

* * *. These are identified in Failure 

Conditions for which an unacceptable 

probability of ignition risk could exist if 

specific tasks and/or practices are not 

performed in accordance with the corrective 

actions(s) developed by the TC [type 

certificate] holder. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

December 10, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 10, 2010. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

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68186 Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations 

FOR FURTHER INFORMATION CONTACT: 

Shahram Daneshmandi, Aerospace 

Engineer, International Branch, ANM– 

116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1112; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 29, 2010 (75 FR 37339), 

and proposed to supersede AD 2008– 

09–22, Amendment 39–15503 (73 FR 

23939, May 1, 2008). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Prompted by [an] accident * * *, the FAA 

published SFAR 88 (Special Federal Aviation 

Regulation 88). Subsequently, the Joint 

Aviation Authorities (JAA) recommended the 

application of a similar regulation to the 

National Aviation Authorities (NAA) of its 

member countries. 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. 

In August 2005, EASA published a policy 

statement on the process for developing 

instructions for maintenance and inspection 

of Fuel Tank System ignition source 

prevention (EASA D 2005/CPRO), that also 

included the EASA expectations with regard 

to compliance times of the corrective actions 

on the unsafe and the not unsafe part of the 

harmonised design review results. 

Fuel Airworthiness Limitations arising 

from the required systems safety analysis are 

items that have been shown to have failure 

mode(s) associated with an ‘unsafe condition’ 

as defined in the FAA memo 2003–112–15 

‘SFAR 88—Mandatory Action Decision 

Criteria’. These are identified in Failure 

Conditions for which an unacceptable 

probability of ignition risk could exist if 

specific tasks and/or practices are not 

performed in accordance with the corrective 

action(s) developed by the TC [type 

certificate] holder. 

To address these potential unsafe 

conditions, EASA issued AD 2007–0007, 

mandating the Fuel System Airworthiness 

Limitations, comprising maintenance and 

inspection tasks and Critical Design 

Configuration Control Limitations (CDCCL) 

that were, at that moment, defined in issue 

C of EADS–CASA document DT–0–C00– 

05001. That document has now been revised 

and updated to issue D. 

For the reasons described above, this EASA 

AD retains the requirements of AD 2007– 

0007, which is superseded [and corresponds 

to FAA AD 2008–09–22], and requires the 

implementation of the revised Fuel 

Airworthiness Limitations contained in issue 

D of EADS–CASA document DT–0–C00– 

05001 and accomplishment of related 

modifications. 

The required actions are retaining the 

limitations for fuel tank systems, adding 

thermal insulation to the air condition 

compression system, applying double 

bonding connection on fuel tubes, and 

modifying the separation between the 

center wing electrical harness and fuel 

tubes. The application of double 

bonding connections on fuel tubes 

includes doing general visual 

inspections for damage of the inside of 

the fuel tanks, and corrective actions if 

necessary. The corrective actions 

include contacting EADS CASA for 

repair instructions and doing the repair. 

You may obtain further information by 

examining the MCAI in the AD docket. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Corrections to Table 1 of This AD 

In the NPRM, the reference to Eaton 

Component Maintenance Manual 

(CMM) with Illustrated Parts List 28– 

10–63, Revision 003, dated June 20, 

2006, was incorrectly published as 

Eaton CMM with Illustrated Parts List 

28–0–63. This final rule refers to Eaton 

CMM with Illustrated Parts List 28–10– 

63. 

We have changed Table 1 of this AD 

to fix a typographical error, which is 

specified in EADS CASA CMM with 

Illustrated Parts List 28–21–12, Revision 

003, dated June 15, 2007. The title page 

of that document specifies ‘‘Revision 

002.’’ The correct revision level is 

‘‘Revision 003.’’ 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

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 required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 8 products of U.S. registry. 

The actions that are required by AD 

2008–09–22 and retained in this AD 

take about 1 work-hour per product, at 

an average labor rate of $85 per workhour. Based on these figures, the 

estimated cost of the currently required 

actions is $85 per product. 

We estimate that it will take about 90 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of this AD to the U.S. 

operators to be $61,200, or $7,650 per 

product, depending on airplane 

configuration. 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 AD: 

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Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations 68187 

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 AD and placed it in the AD docket. 

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 the NPRM, 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 39–15503 (73 FR 

23939, May 1, 2008) and adding the 

following new AD: 

2010–23–05 EADS CASA (Type Certificate 

Previously Held by Construcciones 

Aeronauticas, S.A.): Amendment 39– 

16494. Docket No. FAA–2010–0640; 

Directorate Identifier 2009–NM–142–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective December 10, 2010. 

Affected ADs 

(b) This AD supersedes AD 2008–09–22, 

Amendment 39–15503. 

Applicability 

(c) This AD applies to EADS CASA (Type 

Certificate previously held by Construcciones 

Aeronauticas, S.A.) Model CN–235, CN–235– 

100, CN–235–200, and CN–235–300 

airplanes, and Model C–295 airplanes, all 

serial numbers; certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Prompted by [an] accident * * *, the FAA 

published SFAR 88 (Special Federal Aviation 

Regulation 88). Subsequently, the Joint 

Aviation Authorities (JAA) recommended the 

application of a similar regulation to the 

National Aviation Authorities (NAA) of its 

member countries. 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. 

In August 2005, EASA [European Aviation 

Safety Agency] published a policy statement 

on the process for developing instructions for 

maintenance and inspection of Fuel Tank 

System ignition source prevention (EASA D 

2005/CPRO), that also included the EASA 

expectations with regard to compliance times 

of the corrective actions on the unsafe and 

the not unsafe part of the harmonised design 

review results. 

Fuel Airworthiness Limitations arising 

from the required systems safety analysis are 

items that have been shown to have failure 

mode(s) associated with an ‘unsafe condition’ 

as defined in the FAA memo 2003–112–15 

‘SFAR 88—Mandatory Action Decision 

Criteria’. These are identified in Failure 

Conditions for which an unacceptable 

probability of ignition risk could exist if 

specific tasks and/or practices are not 

performed in accordance with the corrective 

action(s) developed by the TC [type 

certificate] holder. 

To address these potential unsafe 

conditions, EASA issued AD 2007–0007, 

mandating the Fuel System Airworthiness 

Limitations, comprising maintenance and 

inspection tasks and Critical Design 

Configuration Control Limitations (CDCCL) 

that were, at that moment, defined in issue 

C of EADS–CASA document DT–0–C00– 

05001. That document has now been revised 

and updated to issue D. 

For the reasons described above, this EASA 

AD retains the requirements of AD 2007– 

0007, which is superseded [and corresponds 

to FAA AD 2008–09–22], and requires the 

implementation of the revised Fuel 

Airworthiness Limitations contained in issue 

D of EADS–CASA document DT–0–C00– 

05001 and accomplishment of related 

modifications. 

The required actions are retaining the 

limitations for fuel tank systems, adding 

thermal insulation to the air condition 

compression system, applying double 

bonding connection on fuel tubes, and 

modifying the separation between the center 

wing electrical harness and fuel tubes. The 

application of double bonding connections 

on fuel tubes includes doing general visual 

inspections for damage of the inside of the 

fuel tanks, and corrective actions if 

necessary. The corrective actions include 

contacting EADS CASA for repair 

instructions and doing the repair. You may 

obtain further information by examining the 

MCAI in the AD docket. 

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– 

09–22, With Revised Paragraph Formatting 

(g) Do the following actions. 

(1) Within 6 months after June 5, 2008 (the 

effective date of AD 2008–09–22), do the 

revisions specified in (g)(1)(i) or (g)(1)(ii) of 

this AD. 

(i) Revise the Airworthiness Limitations 

section of the Instructions for Continued 

Airworthiness to include the CDCCL data 

using a method approved in accordance with 

the procedures specified in paragraph (i)(1) 

of this AD. 

(ii) Revise the Airworthiness Limitations 

section of the Instructions for Continued 

Airworthiness by incorporating the 

information in EADS CASA CN–235/C–295 

Technical Document DT–0–C00–05001, Issue 

C, dated October 2006. Where this EADS 

CASA technical document refers to an EADS 

CASA component maintenance manual 

(CMM), use the applicable CMM specified in 

Table 1 of this AD. 

TABLE 1—APPLICABLE CMMS

CDCCL 

number CDCCL description CMM Revision Date 

8 .................... Fuel pumps ................................ Parker Hannifin CMM with Illustrated Parts List 28– 

22–12 (replaces CM 1C12–34).

5 January 10, 2008. 

8 .................... Centrifugal fuel boost pump ...... Parker Hannifin CMM with Illustrated Parts List CM 

1C7–20, –21 (replaces CMM RR54170).

B November 20, 2006. 

9 .................... Low level sensor ........................ EADS CASA CMM with Illustrated Parts List 28–21– 

12.

003 June 15, 2007. 

10 .................. 3/4′′ shutoff motorized valve ...... Eaton CMM with Illustrated Parts List 28–20–81 ......... 2 June 20, 2006. 

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68188 Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations 

TABLE 1—APPLICABLE CMMS—Continued 

CDCCL 

number CDCCL description CMM Revision Date 

11 .................. 2′′ motorized spherical plug 

pressure relief valve.

Eaton CMM with Illustrated Parts List 28–10–63 ......... 3 June 20, 2006. 

12 .................. Signal conditioner ...................... Gull CMM with Illustrated Parts List 28–40–61 ............ 3 June 28, 2007. 

13 .................. Fuel control unit ......................... Zodiac Intertechnique CMM with Illustrated Parts List 

28–41–05.

3 September 25, 2006. 

Note 1: Table 1 of this AD does not include 

CMMs 28–22–15, CE 400150–E01, and C 

17MQ0020–005SE, which are listed in EADS 

CASA CN–235/C–295 Technical Document 

DT–0–C00–05001, Issue C, dated October 

2006. These CMM document numbers no 

longer apply. In addition, CMM document 

number 28–21–81 in EADS CASA CN–235/ 

C–295 Technical Document DT–0–C00– 

05001, Issue C, dated October 2006, should 

be CMM document number 28–20–81. 

(2) After accomplishing the actions 

specified in paragraph (g)(1) of this AD, no 

alternative CDCCLs may be used unless the 

CDCCLs are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (i)(1) of this AD. 

New Requirements of This AD 

(h) Do the following actions. 

(1) Within 3 months after the effective date 

of this AD, revise the Airworthiness 

Limitations section of the Instructions for 

Continued Airworthiness by incorporating 

the information in EADS CASA CN–235/C– 

295 Technical Document DT–0–C00–05001, 

Issue D, dated October 2008. Where this 

EADS CASA technical document refers to an 

EADS CASA CMM, use the applicable CMM 

specified in Table 1 of this AD. Doing this 

revision terminates the requirements 

specified in paragraph (g) of this AD. 

Note 2: Notwithstanding any other 

maintenance or operational requirements, 

components that have been identified as 

airworthy or installed on the affected 

airplanes before the revision of the fuel 

airworthiness limitations, as required by 

paragraphs (g) and (h) of this AD, do not need 

to be reworked in accordance with the 

CDCCLs. However, once the fuel 

airworthiness limitations have been revised, 

future maintenance actions on these 

components must be done in accordance 

with the CDCCLs. 

(2) After accomplishing the actions 

specified in paragraph (h)(1) of this AD, no 

alternative CDCCLs may be used unless the 

CDCCLs are approved as an AMOC in 

accordance with the procedures specified in 

paragraph (i)(1) of this AD. 

(3) Within 6 months after the effective date 

of this AD, accomplish the modifications 

specified in paragraphs (h)(3)(i), (h)(3)(ii), 

and (h)(3)(iii) of this AD, as applicable. 

(i) For Model CN–235, CN–235–200, and 

CN–235–300 airplanes having serial numbers 

identified in EADS CASA Service Bulletin 

SB–235–21–18, dated August 2, 2007: Add 

thermal insulation to the air condition 

compression system, in accordance with the 

Accomplishment Instructions of EADS CASA 

Service Bulletin SB–235–21–18, dated 

August 2, 2007. 

(ii) For Model CN–235, CN–235–200, and 

CN–235–300 airplanes having serial numbers 

identified in EADS CASA Service Bulletin 

SB–235–28–18, dated August 2, 2007: Apply 

double bonding connections on fuel tubes 

and do general visual inspections for damage 

inside of the tank, in accordance with the 

Accomplishment Instructions of EADS CASA 

Service Bulletin SB–235–28–18, dated 

August 2, 2007. If any damage is found inside 

the tank, before further flight, contact EADS 

CASA for repair instructions and do the 

repair. 

(iii) For Model CN–235, CN–235–200, and 

CN–235–300 airplanes having serial numbers 

identified in EADS CASA Service Bulletin 

SB–235–24–20, dated August 2, 2007: Modify 

the separation between the center wing 

electrical harnesses and fuel tubes, in 

accordance with the Accomplishment 

Instructions of EADS CASA Service Bulletin 

SB–235–24–20, dated August 2, 2007. 

FAA AD Difference 

Note 3: This AD differs from the MCAI 

and/or service information as follows: 

(1) The European Aviation Safety Agency 

(EASA) AD 2009–0146, dated July 3, 2009, 

inadvertently refers to the incorrect service 

bulletins. For applying double bonding 

connections on fuel tubes and doing general 

visual inspections for damage inside the 

tank, we refer to EADS CASA Service 

Bulletin SB–235–28–18, dated August 2, 

2007. For modifying the separation between 

the center wing electrical harnesses and fuel 

tubes, we refer to EADS CASA Service 

Bulletin SB–235–24–20, dated August 2, 

2007. 

(2) The EASA AD 2009–0146, dated July 3, 

2009; and EADS CASA Service Bulletin SB– 

235–28–18, dated August 2, 2007; do not 

specify corrective actions if any damage is 

found inside the tank. If any damage is found 

inside the tank, this AD requires contacting 

EADS CASA for repair instructions and 

doing the repair. 

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: Shahram 

Daneshmandi, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1112; 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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(j) Refer to MCAI EASA Airworthiness 

Directive 2009–0146, dated July 3, 2009, the 

CMMs identified in Table 1 of this AD, and 

the service information identified in Table 2 

of this AD, for related information. 

TABLE 2—SERVICE INFORMATION

Document Issue Date 

EADS CASA Service Bulletin SB–235–21–18 ..................................................................... Original ................................. August 2, 2007. 

EADS CASA Service Bulletin SB–235–24–20 ..................................................................... Original ................................. August 2, 2007. 

EADS CASA Service Bulletin SB–235–28–18 ..................................................................... Original ................................. August 2, 2007. 

EADS CASA CN–235/C–295 Technical Document DT-0-C00-05001 ................................. Issue C ................................. October 2006. 

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Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations 68189 

TABLE 2—SERVICE INFORMATION—Continued 

Document Issue Date 

EADS CASA CN–235/C–295 Technical Document, DT–0–C00–05001 ............................. Issue D ................................. October 2008. 

Material Incorporated by Reference 

(k) You must use the service information 

contained in Table 3 of this AD to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact EADS–CASA, Military 

Transport Aircraft Division (MTAD), 

Integrated Customer Services (ICS), 

Technical Services, Avenida de Arago ́n 404, 

28022 Madrid, Spain; telephone +34 91 585 

55 84; fax +34 91 585 55 05; e-mail 

MTA.TechnicalService@casa.eads.net; 

Internet http://www.eads.net. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

TABLE 3—MATERIAL INCORPORATED BY REFERENCE

Document Revision/issue Date 

EADS CASA CMM with Illustrated Parts List 28–21–12 ..................................................... Revision 003 ......................... June 15, 2007. 

EADS CASA CN–235/C–295 Technical Document DT–0–C00–05001 .............................. Issue C ................................. October 2006. 

EADS CASA CN–235/C–295 Technical Document DT–0–C00–05001 .............................. Issue D ................................. October 2008. 

EADS CASA Service Bulletin SB–235–21–18 ..................................................................... Original ................................. August 2, 2007. 

EADS CASA Service Bulletin SB–235–24–20 ..................................................................... Original ................................. August 2, 2007. 

EADS CASA Service Bulletin SB–235–28–18 ..................................................................... Original ................................. August 2, 2007. 

Eaton CMM with Illustrated Parts List 28–10–63 ................................................................. Revision 3 ............................. June 20, 2006. 

Eaton CMM with Illustrated Parts List 28–20–81 ................................................................. Revision 2 ............................. June 20, 2006. 

Gull CMM with Illustrated Parts List 28–40–61 .................................................................... Revision 3 ............................. June 28, 2007. 

Parker Hannifin CMM with Illustrated Parts List 28–22–12 ................................................. Revision 5 ............................. January 10, 2008. 

Parker Hannifin CMM with Illustrated Parts List CM 1C7–20, –21 ..................................... Revision B ............................ November 20, 2006. 

Zodiac Intertechnique CMM with Illustrated Parts List 28–41–05 ....................................... Revision 3 ............................. September 25, 2006. 

(The title page of EADS CASA CMM with 

Illustrated Parts List 28–21–12 contains an 

incorrect revision level; the correct revision 

level is 003. The issue date of EADS CASA 

CN–235/C–295 Technical Document DT–0– 

C00–05001, Issue C; and EADS CASA CN– 

235/C–295 Technical Document DT–0–C00– 

05001, Issue D; can only be found on the title 

page and in the Revisions Record. Certain 

pages of EADS CASA Service Bulletin SB– 

235–28–18 have missing or incomplete 

document numbers and dates; the correct 

document number and dates for those pages 

can be found on the first page of that 

document. The date shown on the List of 

Effective Pages for Eaton CMM with 

Illustrated Parts List 28–10–63, and Eaton 

CMM with Illustrated Parts List 28–20–81, is 

incorrect; the correct date for that page of 

those documents is June 20, 2006. The 

revision level shown on page 7 of Parker 

Hannifin CMM with Illustrated Parts List CM 

1C7–20, –21 (replaces CMM RR54170), is 

incorrect; the correct revision level for that 

page is B. The revision level of EADS CASA 

CN–235/C–295 Technical Document DT–0– 

C00–05001, Issue C; EADS CASA CN–235/C– 

295 Technical Document DT–0–C00–05001, 

Issue D; and Eaton CMM with Illustrated 

Parts List 28–20–81; is located only in the 

Record of Revisions for those documents.) 

Issued in Renton, Washington, on October 

20, 2010. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–27615 Filed 11–4–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 121 

[Docket No. FAA–2009–0022; Amendment 

No.: 121–350] 

RIN 2120–AJ30 

Crewmember Requirements When 

Passengers are Onboard 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: Currently, during passenger 

boarding and deplaning, all flight 

attendants are required to be on board 

the airplane. This final rule will allow 

one required flight attendant to deplane 

during passenger boarding, to conduct 

safety-related duties, as long as certain 

conditions are met. In addition, this rule 

will allow a pilot or flight engineer not 

assigned to the flight to substitute for a 

flight attendant when that flight 

attendant does not remain within the 

immediate vicinity of the door through 

which passengers are boarding. This 

rule will also allow a reduction of flight 

attendants remaining on board the 

airplane during passenger deplaning, as 

long as certain conditions are met. The 

FAA has determined that these 

revisions to current regulations can be 

made as a result of recent safety 

enhancements to airplane equipment 

and procedures. These changes have 

mitigated the risks to passengers during 

ground operations that previously 

required all flight attendants to be on 

board the airplane during passenger 

boarding and deplaning. 

DATES: These amendments become 

effective January 4, 2011. 

FOR FURTHER INFORMATION CONTACT: For 

technical questions concerning this final 

rule contact Nancy Lauck Claussen, Air 

Transportation Division AFS–200, 

Federal Aviation Administration, 800 

Independence Avenue, SW., 

Washington, DC 20591; telephone (202) 

267–8166; facsimile (202) 267–5229, 

e-mail Nancy.L.Claussen@faa.gov. For 

legal questions concerning this final 

rule contact Paul G. Greer, Regulations 

mstockstill on DSKH9S0YB1PROD with RULES