39814 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations 

related investigative and corrective actions, 

in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 777– 

57A0064, Revision 1, dated May 6, 2010, 

except as required by paragraph (i) of this 

AD. Do all applicable related investigative 

and corrective actions at the applicable time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 777–57A0064, 

Revision 1, dated May 6, 2010, except as 

required by paragraph (h) of this AD. 

(2) For airplanes identified as Group 2 

airplanes in Boeing Service Bulletin 777– 

57A0064, Revision 1, dated May 6, 2010: Do 

a detailed inspection of the slat cans at the 

outboard slat number 3 and 12 outboard 

main track locations for holes and wear 

damage and do all applicable corrective 

actions, and replace the downstop hardware 

for the outboard slats number 3 and 12 

outboard and inboard main track locations, 

in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 777– 

57A0064, Revision 1, dated May 6, 2010. Do 

all applicable corrective actions at the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

777–57A0064, Revision 1, dated May 6, 2010. 

Exception to the Service Bulletin 

(h) Where Boeing Service Bulletin 777– 

57A0064, Revision 1, dated May 6, 2010, 

specifies a compliance time after the date on 

the service bulletin, this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(i) Where Boeing Service Bulletin 777– 

57A0064, Revision 1, dated May 6, 2010, 

specifies measuring torque of the nuts of the 

slat main track stop hardware of slats 3 and 

12, this AD does not require that action for 

Group 2 airplanes. 

Credit for Actions Accomplished Previously 

(j) Actions accomplished before the 

effective date of this AD according to Boeing 

Alert Service Bulletin 777–57A0064, dated 

March 26, 2009, are considered acceptable 

for compliance with the corresponding 

actions specified in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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: 

Duong Tran, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6452; fax (425) 917–6590. Or, email information to 9-ANM-Seattle-ACOAMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Material Incorporated by Reference 

(l) You must use Boeing Service Bulletin 

777–57A0064, Revision 1, dated May 6, 2010, 

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 Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.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 June 21, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–16201 Filed 7–12–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1215; Directorate 

Identifier 2009–NM–126–AD; Amendment 

39–16364; AD 2010–14–19] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 and –300, and Model A340– 

200, –300, –500 and –600 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

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: 

* * * [P]artial blockage of the water 

absorbing filter element P/N (part number) 

QA06123 was observed several times. The 

blockage was created by carbon debris from 

the cartridge and from the burst disc of the 

Halon bottle. 

This water absorbing filter element is part 

of Halon Dual-Filter Assembly installed also 

in the Flow Metering System (FMS) of the 

cargo compartment Fire Extinguishing 

System used in the A330 and A340 

aeroplanes. 

Blockage of the water absorbing filter 

element could lead to reduction of Halon 

outflow, leading to incapacity to maintain 

fire extinguishing agent concentration. 

Combined with fire, this could result in an 

uncontrolled fire in the affected 

compartment, which would constitute an 

unsafe condition. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

August 17, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 17, 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. 

FOR FURTHER INFORMATION CONTACT: 

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. 

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 December 29, 2009 (74 FR 

68737). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During the qualification test campaign at 

the supplier site of the prototype Flow 


jlentini on DSKJ8SOYB1PROD with RULES
Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations 39815 

Metering Compact Unit (FMCU) Part Number 

(P/N) QA07907–03, partial blockage of the 

water absorbing filter element P/N QA06123 

was observed several times. The blockage 

was created by carbon debris from the 

cartridge and from the burst disc of the Halon 

bottle. 

This water absorbing filter element is part 

of Halon Dual-Filter Assembly installed also 

in the Flow Metering System (FMS) of the 

cargo compartment Fire Extinguishing 

System used in the A330 and A340 

aeroplanes. 

Blockage of the water absorbing filter 

element could lead to reduction of Halon 

outflow, leading to incapacity to maintain 

fire extinguishing agent concentration. 

Combined with fire, this could result in an 

uncontrolled fire in the affected 

compartment, which would constitute an 

unsafe condition. 

To avoid water absorbing filter element 

blockage, this AD requires replacement [with 

improved dual-filter assemblies] or 

modification of the Halon dual-filter 

assemblies of the lower deck cargo 

compartment fire extinguishing system: 

—In the forward cargo compartment for 

aeroplanes fitted with Lower Deck Cargo 

Compartment (LDCC) and 

—In the bulk cargo compartment for 

aeroplanes fitted with Bulk Cargo Rest 

Compartment (BCRC) fire extinguishing 

system. 

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 

considered the comments received. 

Support for the NPRM 

Delta Air Lines (DAL) supports the 

intent of the NPRM. 

Request To Refer to Updated Revisions 

of Service Information 

Air Transport Association (ATA), on 

behalf of its member DAL, requests that 

we revise paragraph (f) of the NPRM to 

reference the most recent version of 

Airbus Mandatory Service Bulletin 

A330–26–3040 as an acceptable means 

of compliance. 

We agree to refer to Airbus Mandatory 

Service Bulletin A330–26–3040, 

Revision 03, dated November 9, 2009. 

Airbus has also released Mandatory 

Service Bulletin A340–26–4038, 

Revision 03, dated November 9, 2009; 

and Mandatory Service Bulletin A340– 

26–5019, Revision 04, dated December 

11, 2009. The revisions introduce minor 

changes and add the Halon filter part 

number, but do not add any additional 

work. We have revised this final rule 

accordingly. 

Request To Mandate a Specific Version 

of PALL Service Bulletin 

ATA, on behalf of its member DAL, 

states that it will be unable to fully 

comply because of an inconsistency in 

the PALL service information. DAL 

requests that we revise the NPRM to 

mandate a specific issue of PALL 

Service Bulletin 6753–20–2. DAL states 

that specifying a specific issue level is 

necessary because acceptable part 

numbers vary in the work instruction in 

the different issues of this PALL service 

bulletin. 

We disagree. Airbus has issued new 

service information, which specifies the 

specific part number, Halon filter 

having part number QA06753–03VSB or 

QA06753–03. The Airbus service 

information specified in Table 1 of this 

AD refers to PALL Service Bulletin 

6753–20–2 only as an additional source 

of guidance for modifying the Halon 

dual-filter assembly. We have revised 

this final rule to include the latest 

version of the applicable Airbus service 

information and to provide credit for 

work done in accordance with previous 

revisions of the service information. 

Request To Postpone Release of the 

Final Rule Until PALL Service Bulletin 

Is Revised 

ATA, on behalf of its member DAL, 

requests that we postpone releasing the 

final rule until PALL revises its service 

information. DAL states that the 

paragraph 2.D of PALL Service Bulletin 

6753–20–2 specifies when performing 

the modification in situ to continue to 

step 7 after accomplishing an airplane 

leak check. DAL states that PALL 

Service Bulletin 6753–20–2 specifies to 

proceed to step 4 if not performing the 

modification in situ. However, DAL 

notes that steps 2.D.7 and 2.D.8 state to 

remove tooling from the filter assembly, 

which is installed in step 5. DAL notes 

that if the modification is being 

performed in situ, then step 5 is not 

accomplished, and therefore, steps 7 

and 8 cannot be accomplished. 

We do not agree to wait to issue the 

final rule until PALL releases a revised 

service bulletin. However, we agree that 

clarification may be necessary. We have 

coordinated with Airbus, and it has 

confirmed that PALL Service Bulletin 

6753–20–2, Issue 4, dated November 21, 

2009, contains a discrepancy in a note. 

Airbus states that when performing the 

work ‘on-wing,’ operators using PALL 

Service Bulletin 6753–20–2, Issue 4, 

dated November 21, 2009, for guidance 

should go to step 9, not step 7. We have 

not changed the AD in regard to this 

issue. 

Conclusion 

We reviewed the available data, 

including the comments received, 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. 

Explanation of Change to Costs of 

Compliance 

Since issuance of the NPRM, we have 

increased the labor rate used in the 

Costs of Compliance from $80 per workhour to $85 per work-hour. The Costs of 

Compliance information, below, reflects 

this increase in the specified hourly 

labor rate. 

Costs of Compliance 

We estimate that this AD will affect 

32 products of U.S. registry. We also 

estimate that it will take about 13 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $708 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 parts. 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 this AD 

to the U.S. operators to be $58,016, or 

$1,813 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. 


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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: 

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 adding 

the following new AD: 

2010–14–19 Airbus: Amendment 39–16364. 

Docket No. FAA–2009–1215; Directorate 

Identifier 2009–NM–126–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 17, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to airplanes certificated 

in any category, identified in paragraphs 

(c)(1), (c)(2), and (c)(3) of this AD. 

(1) Airbus Model A330–201, –202, –203, 

–223, –243, –301, –302, –303, –321, –322, 

–323, –341, –342 and –343 airplanes, all 

serial numbers, except those on which 

Airbus modification 55590 has been 

embodied in production. 

(2) Airbus Model A340–211, –212, –213, 

–311, –312, –313, –541, and –642 airplanes, 

all serial numbers fitted with lower deck 

cargo compartment (LDCC), except those on 

which Airbus modification 55590 has been 

embodied in production. 

(3) Airbus Model A340–311, –312, –313, 

–541, and –642 airplanes, all serial numbers 

fitted with bulk cargo rest compartment 

(BCRC), except those on which Airbus 

modification 56047 has been embodied in 

production. 

Note 1: The BCRC is embodied in 

production on Model A340–300, A340–500, 

and A340–600 airplanes through the 

following Airbus modification (including but 

not limited to): 47198, 47884, 48895, 48710, 

49136, 50107, 50900, 50901, or 51320. 

Note 2: The fire extinguishing system for 

the BCRC is embodied in production on 

Model A340–500 and A340–600 airplanes 

through Mod 47197 (partial BCRC); on Model 

A340–500 and A340–600 airplanes through 

Mod 47883 (full BCRC); and on Model A340– 

300 airplanes through Mod 50108 (partial 

BCRC). 

Subject 

(d) Air Transport Association (ATA) of 

America Code 26: Fire protection. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During the qualification test campaign at 

the supplier site of the prototype Flow 

Metering Compact Unit (FMCU) Part Number 

(P/N) QA07907–03, partial blockage of the 

water absorbing filter element P/N QA06123 

was observed several times. The blockage 

was created by carbon debris from the 

cartridge and from the burst disc of the Halon 

bottle. 

This water absorbing filter element is part 

of Halon Dual-Filter Assembly installed also 

in the Flow Metering System (FMS) of the 

cargo compartment Fire Extinguishing 

System used in the A330 and A340 

aeroplanes. 

Blockage of the water absorbing filter 

element could lead to reduction of Halon 

outflow, leading to incapacity to maintain 

fire extinguishing agent concentration. 

Combined with fire, this could result in an 

uncontrolled fire in the affected 

compartment, which would constitute an 

unsafe condition. 

To avoid water absorbing filter element 

blockage, this AD requires replacement [with 

improved dual-filter assemblies] or 

modification of the Halon dual-filter 

assemblies of the lower deck cargo 

compartment fire extinguishing system: 

—In the forward cargo compartment for 

aeroplanes fitted with Lower Deck Cargo 

Compartment (LDCC) and 

—In the bulk cargo compartment for 

aeroplanes fitted with Bulk Cargo Rest 

Compartment (BCRC) fire extinguishing 

system. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Replace or modify the Halon dual-filter 

assemblies of the flow metering fire 

extinguishing system in the forward and bulk 

cargo compartments, as applicable, in 

accordance with the Accomplishment 

Instructions of the applicable service bulletin 

identified in Table 1 of this AD, at the 

applicable time specified in paragraphs 

(f)(1)(i), (f)(1)(ii), and (f)(1)(iii) of this AD. 

TABLE 1—SERVICE BULLETINS

Airbus model— Airbus mandatory service bulletin— Revision— Dated— 

A330–200 and –300 airplanes ................................................ A330–26–3040 ....................................... 03 November 9, 2009. 

A340–200 and –300 airplanes ................................................ A340–26–4038 ....................................... 03 November 9, 2009. 

A340–500 and –600 airplanes ................................................ A340–26–5019 ....................................... 04 December 11, 2009. 


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Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations 39817 

(i) For airplanes fitted with Halon dualfilter assemblies part number (P/N) QA06753: 

Within 18 months after the effective date of 

this AD. 

(ii) For Model A340–642 series airplanes, 

weight variant 101, 102, and 103 fitted with 

Halon dual-filter assembly P/N QA06753–01 

or P/N QA06753–02: Within 18 months after 

the effective date of this AD. 

(iii) For airplanes other than those 

identified in paragraph (f)(1)(ii) of this AD 

and fitted with Halon dual-filter assembly 

P/N QA06753–01 or P/N QA06753–02: 

Within 24 months after the effective date of 

this AD. 

Note 3: The Halon dual-filter assembly 

P/N QA06753 is embodied in production 

through Airbus modification 40041. The 

Halon dual-filter assembly P/N QA06753–01 

is only embodied in service through Airbus 

Service Bulletin A330–26–3030 or Airbus 

Service Bulletin A340–26–4038. The Halon 

dual-filter assembly P/N QA06753–02 is 

embodied in production through 

modification 47197 or 47883 or 50108 

(BCRC) and 51065 or 51329 (LDCC) or in 

service through Airbus Service Bulletin 

A330–26–3030 or Airbus Service Bulletin 

A340–26–4038. 

(2) Actions accomplished before the 

effective date of this AD according to the 

service bulletins listed in Table 2 of this AD 

are considered acceptable for compliance 

with the corresponding actions specified in 

this AD. 

TABLE 2—CREDIT SERVICE BULLETINS

Airbus— Revision— Dated— 

Mandatory Service Bulletin A330–26–3040 ............................................................................................. 02 ..................... August 6, 2008. 

Mandatory Service Bulletin A340–26–5019 ............................................................................................. 02 ..................... August 6, 2008. 

Mandatory Service Bulletin A340–26–5019 ............................................................................................. 03 ..................... May 19, 2009. 

Service Bulletin A330–26–3040 ............................................................................................................... Original ............. March 29, 2007. 

Service Bulletin A330–26–3040 ............................................................................................................... 01 ..................... December 19, 2007. 

Service Bulletin A340–26–4038 ............................................................................................................... Original ............. March 29, 2007. 

Service Bulletin A340–26–4038 ............................................................................................................... 01 ..................... December 19, 2007. 

Service Bulletin A340–26–4038 ............................................................................................................... 02 ..................... August 6, 2008. 

Service Bulletin A340–26–5019 ............................................................................................................... Original ............. July 27, 2007. 

Service Bulletin A340–26–5019 ............................................................................................................... 01 ..................... January 23, 2008. 

FAA AD Differences 

Note 4: This AD differs from the MCAI 

and/or service information as follows: 

(1) The second paragraph of the 

applicability of the MCAI specifies certain 

models except those on which Modification 

55590 has been done. Paragraph (c)(2) of this 

AD specifies those models fitted with lower 

deck cargo compartment (LDCC), except 

those on which Modification 55590 has been 

done. 

(2) Although the MCAI tells you to submit 

information to the manufacturer, this AD 

does not require such a submittal. 

Other FAA AD Provisions 

(g) 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: 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 

(h) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2009– 

0064, dated March 12, 2009, and the service 

information identified in Table 3 of this AD, 

for related information. 

TABLE 3—RELATED SERVICE INFORMATION

Airbus mandatory service bulletin— Revision— Dated— 

A330–26–3040 ................................................................................................................................................... 03 November 9, 2009. 

A340–26–4038 ................................................................................................................................................... 03 November 9, 2009. 

A340–26–5019 ................................................................................................................................................... 04 December 11, 2009. 

Material Incorporated by Reference 

(i) You must use the service information 

contained in Table 4 of this AD to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

TABLE 4—MATERIAL INCORPORATED BY REFERENCE

Airbus mandatory service bulletin— Revision— Dated— 

A330–26–3040 ................................................................................................................................................... 03 November 9, 2009. 

A340–26–4038 ................................................................................................................................................... 03 November 9, 2009. 

A340–26–5019 ................................................................................................................................................... 04 December 11, 2009. 

(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 SAS—Airworthiness 


jlentini on DSKJ8SOYB1PROD with RULES
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Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80, e-mail 

airworthiness.A330-A340@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 June 29, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–16550 Filed 7–12–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0383; Directorate 

Identifier 2009–NM–214–AD; Amendment 

39–16362; AD 2010–14–17] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747SR, 

and 747SP Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747–400, 747SR, and 747SP 

series airplanes. This AD requires 

repetitive detailed inspections of certain 

overwing intercostal webs, and related 

investigative and corrective actions if 

necessary. This AD results from reports 

of cracks in overwing intercostal webs. 

We are issuing this AD to detect and 

correct such cracking, which could grow 

and result in a severed intercostal. If an 

intercostal is severed, cracks could 

develop in the adjacent frame structure 

and skin, resulting in a rapid loss of 

cabin pressure. 

DATES: This AD is effective August 17, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 17, 2010. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to 

certain Model 747–100, 747–100B, 747– 

100B SUD, 747–200B, 747–200C, 747– 

200F, 747–300, 747–400, 747SR, and 

747SP series airplanes. That NPRM was 

published in the Federal Register on 

April 21, 2010 (75 FR 20792). That 

NPRM proposed to require repetitive 

detailed inspections of certain overwing 

intercostal webs, and related 

investigative and corrective actions if 

necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Boeing supports the NPRM. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 86 

airplanes of U.S. registry. The following 

table provides the estimated costs for 

U.S. operators to comply with this AD. 

TABLE—ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts Cost per product 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection ... 4 $85 None ........... $340 per inspection cycle 86 $29,240 per inspection cycle. 

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 

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 


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