Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations 39811 

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: Louis 

Natsiopoulos, Aerospace Engineer, Systems 

and Equipment Branch, ANM–130S, 1601 

Lind Avenue SW., Renton, Washington 

98057–3356; telephone (425) 917–6478; fax 

(425) 917–6590. Information may be e-mailed 

to: 9-ANM-Seattle-ACO-AMOCRequests@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. 

Material Incorporated by Reference 

(l) You must use the applicable service 

information contained in Table 3 of this AD 

to do the actions required by this AD, unless 

the AD specifies otherwise. If you 

accomplish the optional actions specified by 

this AD, you must use the applicable service 

information specified in Table 3 of this AD 

to perform those actions, 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. 

TABLE 3—MATERIAL INCORPORATED BY REFERENCE

Boeing Special Attention Service Bulletin— Revision— Dated— 

757–30–0019 .......................................................................................................... 2 ............................................................. April 19, 2010. 

757-30-0020 ........................................................................................................... 2 ............................................................. March 31, 2010. 

767-30–0039 ........................................................................................................... Original .................................................. December 5, 2007. 

767–30–0041 .......................................................................................................... Original .................................................. December 5, 2007. 

777–30–0012 .......................................................................................................... 2 ............................................................. December 19, 2007. 

Issued in Renton, Washington, on July 6, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–17046 Filed 7–9–10; 4:15 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1249; Directorate 

Identifier 2009–NM–100–AD; Amendment 

39–16358; AD 2010–14–13] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 777 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Model 777 airplanes. This AD requires 

inspecting the bolt, nut, and downstop 

of the slat track assembly to determine 

if the bolt, nut, or stops are missing and 

to determine if the thread protrusion of 

the bolt from the nut is within specified 

limits and parts are correctly installed, 

and related investigative and corrective 

actions if necessary. For certain 

airplanes, this AD also requires 

inspecting the slat cans at the outboard 

slat number 3 and 12 outboard main 

track locations for holes and wear 

damage, and corrective actions if 

necessary; and replacing the downstop 

hardware for the outboard slats number 

3 and 12 outboard and inboard main 

track locations. This AD results from a 

report of a hole in the inboard main 

track slat can for outboard slat number 

12 on a Model 777 airplane. The hole 

was caused when the bolt securing the 

downstop migrated out of the fitting and 

contacted the slat can. We are issuing 

this AD to detect and correct damage to 

the outboard slat main track slat cans, 

which can allow fuel leakage into the 

fixed wing leading edge in excess of the 

capacity of the draining system. Excess 

fuel leakage could result in an 

uncontained fire. 

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: 

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. 

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 777 airplanes. That 

NPRM was published in the Federal 

Register on January 7, 2010 (75 FR 950). 

That NPRM proposed to require 

inspecting the bolt, nut, and downstop 

of the slat track assembly to determine 


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39812 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations 

if the bolt, nut, or stops are missing and 

to determine if the thread protrusion of 

the bolt from the nut is within specified 

limits and parts are correctly installed, 

and related investigative and corrective 

actions if necessary. For certain 

airplanes, that NPRM also proposed to 

require inspecting the slat cans at the 

outboard slat number 3 and 12 outboard 

main track locations for holes and wear 

damage, and corrective actions if 

necessary; and replacing the downstop 

hardware for the outboard slats number 

3 and 12 outboard and inboard main 

track locations. 

Relevant Service Information 

We have reviewed Boeing Service 

Bulletin 777–57A0064, Revision 1, 

dated May 6, 2010. The NPRM referred 

to Boeing Alert Service Bulletin 777– 

57A0064, dated March 26, 2009, as the 

appropriate source of service 

information. Boeing Service Bulletin 

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

2010, clarifies procedures, deletes a 

requirement, adds a note to allow a 

different fastener, revises an incorrect 

chamfer callout, and adds information 

that was published in Boeing 

Information Notice 777–57A0064 IN 01 

and 777–57A0064 IN 02. Boeing Service 

Bulletin 777–57A0064, Revision 1, 

dated May 6, 2010, does not require 

additional work. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received from 

the commenters. 

Support for the NPRM 

Continental Airlines (Continental) 

supports the intent of the NPRM. 

Request To Add Exception for Group 1 

Airplanes 

Boeing requests that we revise the 

NPRM to add a statement to paragraph 

(h) of the NPRM stating, ‘‘The outboard 

main track locations for slats 3 and 12 

are excluded from the inspection 

defined in Table 3 of Boeing Alert 

Service Bulletin 777–57A0064, dated 

March 26, 2009.’’ Boeing states that, for 

Group 1 airplanes, the slat tracks do not 

penetrate into the wing fuel tank at 

these locations. Boeing also states that, 

for all Group 2 airplanes, this inspection 

is accomplished via Table 4 of Boeing 

Alert Service Bulletin 777–57A0064, 

dated March 26, 2009. Boeing Alert 

Service Bulletin 777–57A0064, dated 

March 26, 2009, states that for only 

Group 2 airplanes the outboard main 

track locations at slats 3 and 12 must be 

inspected. Boeing notes that it plans to 

issue a new revision to this service 

bulletin in June 2010 that contains this 

information. 

We disagree with the commenter that 

such a revision is necessary. We have 

updated this final rule to refer to Boeing 

Service Bulletin 777–57A0064, Revision 

1, dated May 6, 2010. Boeing Service 

Bulletin 777–57A0064, Revision 1, 

dated May 6, 2010, has corrected this 

information. We have added Boeing 

Service Bulletin 777–57A0064, Revision 

1, dated May 6, 2010, as the appropriate 

source of service information for the 

actions required by this AD, including 

paragraph (g)(2) of this AD (in paragraph 

(g)(2) of the NPRM we referred to the 

original issue of the service bulletin for 

the compliance times but did not 

specifically reference the service 

bulletin as the applicable source of 

service information for doing the 

actions). We have also added paragraph 

(j) to this final rule to provide credit for 

actions done in accordance with Boeing 

Alert Service Bulletin 777–57A0064, 

dated March 26, 2009. 

Request To Add Exception for Group 2 

Airplanes 

Boeing further requests that we revise 

paragraph (h) of the NPRM to state, ‘‘For 

airplanes defined as Group 2 in Boeing 

Alert Service Bulletin 777–57A0064, 

dated March 26, 2009, it is not 

necessary to perform the torque check 

on the downstop hardware for slats 3 

and 12 as defined in Table 2 of Boeing 

Alert Service Bulletin 777–57A0064, 

dated March 26, 2009.’’ Boeing states 

that at locations where a fastener is to 

be replaced by subsequent instructions 

in Boeing Alert Service Bulletin 777– 

57A0064, dated March 26, 2009, a 

torque check is redundant and is not a 

technical requirement. Boeing states 

that the visual inspections are still in 

place to guarantee that damage caused 

by a loose fastener will be caught. 

Boeing also adds that Boeing Alert 

Service Bulletin 777–57A0064, dated 

March 26, 2009, specifies compliance 

times for the fastener replacement that 

are less than those for the torque check. 

Boeing notes that it plans to issue a new 

revision to this service bulletin in June 

2010 that contains this information. 

We agree with the commenter that 

such a revision is necessary. We have 

updated this final rule to refer to Boeing 

Service Bulletin 777–57A0064, Revision 

1, dated May 6, 2010. However, we have 

added a new paragraph (i) to this final 

rule to clarify that this measurement is 

not necessary on slats 3 and 12. We 

have added Boeing Service Bulletin 

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

2010, as the primary source of service 

information for accomplishing the 

actions required by this AD. 

Request To Increase the Inspection 

Threshold to 12 Months 

Continental requests that we revise 

the compliance time for the inspection 

from 6 months to 12 months after the 

effective date of the AD. Continental 

states that the current 6-month 

compliance time will not provide a 

practical period in which to complete 

the full inspection for its Model 777 

fleet based on their maintenance 

schedule. Continental states that a 12- 

month threshold would not compromise 

the safety of the airplane because there 

are existing zonal inspection 

requirements in the referenced 

Maintenance Planning Document/ 

Maintenance Review Board (MPD/MRB) 

tasks, discrepancies in the area of 

interest could be detected through the 

required routine inspections. 

Continental states that with a frequency 

of every 1,125 days from delivery, most 

affected airplanes should have had at 

least one inspection performed in 

accordance with the MPD/MRB tasks. 

We disagree. Due to the urgent nature 

of a potential excessive fuel leakage, we 

do not find it appropriate to revise the 

inspection threshold. Furthermore, the 

MPD/MRB zonal inspection 

requirements are not intense enough to 

detect certain unobvious discrepancies 

(e.g., loose bolts and insufficient nut 

torque). However, under the provisions 

of paragraph (k) of this AD, we will 

consider requests for approval of an 

extension of the compliance time if 

sufficient data are submitted to 

substantiate that the extension would 

provide an acceptable level of safety. 

We have not changed the AD in regard 

to this issue. 

Request To Clarify Requirements of 

Downstop Fitting Rework 

EVA Airlines requests that we 

incorporate the information from Boeing 

Information Notice 777–57A0064 IN 01, 

dated May 28, 2009, which states that 

the chamfer for the ¥2 stop fitting in 

view B–B of Appendix A of Boeing 

Alert Service Bulletin 777–57A0064, 

dated March 26, 2009, should be 

‘‘0.820¥0.850 × 90 Degrees¥120 

Degrees’’ instead of ‘‘0.820¥0.050 × 90 

Degrees¥120 Degrees.’’ 

We agree that this information should 

be incorporated into the AD. Boeing 

Service Bulletin 777–57A0064, Revision 

1, dated May 6, 2010, corrects this 

information. As stated previously, we 

have changed this AD to refer to Boeing 

Service Bulletin 777–57A0064, Revision 

1, dated May 6, 2010, as the primary 

source of service information for 

accomplishing the actions required by 

this AD. 


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Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

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 would affect 

129 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 for Group 1 airplanes.39 $85 $0 $3,315 per inspection 

cycle.

127 $421,005 per inspection cycle. 

Inspection for Group 2 airplanes.55 85 0 4,675 per inspection 

cycle.

2 9,350 per inspection cycle. 

Replacement for Group 2 airplanes.8 85 9,267 9,947 ............... 2 19,894. 

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 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

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: 

2010–14–13 The Boeing Company: 

Amendment 39–16358. Docket No. 

FAA–2009–1249; Directorate Identifier 

2009–NM–100–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective August 17, 2010. 

Affected Ads 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 777–200, -200LR, -300, and 

-300ER airplanes, certificated in any 

category; as identified in Boeing Service 

Bulletin 777–57A0064, Revision 1, dated 

May 6, 2010. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Unsafe Condition 

(e) This AD results from a report of a hole 

in the inboard main track slat can for 

outboard slat number 12 on a Model 777 

airplane. The Federal Aviation 

Administration is issuing this AD to detect 

and correct damage to the outboard slat main 

track slat cans, which can allow fuel leakage 

into the fixed wing leading edge in excess of 

the capacity of the draining system. Excess 

fuel leakage could result in an uncontained 

fire. 

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. 

Inspect the Slat Main Track Stop Hardware 

and Measure the Torque of the Slat Main 

Track Stop Hardware 

(g) 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: Do the applicable 

actions specified in paragraphs (g)(1) and 

(g)(2) of this AD. 

(1) For all airplanes: Do a detailed 

inspection of the slat main track stop 

hardware to determine if the bolt, nut, or 

stops are missing and to determine if the 

thread protrusion of the bolt from the nut is 

within specified limits, and do all applicable 


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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 


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