56258 Federal Register / Vol. 72, No. 191 / Wednesday, October 3, 2007 / Rules and Regulations 

In the incorrect formula, an ‘‘×’’

(multiplication) has been replaced with a ‘‘+’’

(addition) when the data was converted in 

the system and if this formula is followed, 

you may receive a result outside of the 

allowed tolerance. 

Incorrect balance, outside the tolerance of 

the aileron control surface, may lead to 

vibrations that in [the] worst case can result 

in flutter. 

The hard copy of the manual, SAAB 2000 

SRM, is correct. 

The CD/DVD dated Oct 01/05, marked 

‘‘Reissue’’, includes a correct SAAB SRM 

revision 22. 

The corrective action includes identifying 

ailerons that have been balanced after July 4, 

2005, until the effective date of this AD. If 

balanced incorrectly, they must be 

rebalanced. 

Actions and Compliance 

(f) Within one month after the effective 

date of this AD, unless already done, do the 

following actions. 

(1) Identify ailerons that have been 

balanced after July 4, 2005. If balanced 

incorrectly, they must be rebalanced before 

further flight in accordance with Saab 

Service Bulletin 2000–57–040, dated 

February 23, 2006. 

(2) As of the effective date of this AD, the 

aileron balancing procedure contained in the 

CD/DVD ‘‘Issue Date: Apr 01/05’’ including 

the Saab SAAB 2000 SRM at Revision 21 and 

the CD/DVD ‘‘Issue Date: Oct 01/05’’

including SRM at Revision 22 may not be 

used. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

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, 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: Mike Borfitz, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 227–

2677; fax (425) 227–1149. Before using any 

approved AMOC on any airplane to which 

the AMOC applies, notify your appropriate 

principal inspector (PI) in the FAA Flight 

Standards District Office (FSDO), or lacking 

a PI, your local FSDO. 

(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, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency Emergency Airworthiness 

Directive 2006–0053–E, dated February 22, 

2006, and Saab Service Bulletin 2000–57–

040, dated February 23, 2006. 

Material Incorporated by Reference 

(i) You must use Saab Service Bulletin 

2000–57–040, dated February 23, 2006, 

including Attachment 1, dated April 1, 2006, 

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 Saab Aircraft AB, SAAB 

Aircraft Product Support, S–581.88, 

Linko ̈ping, Sweden. 

(3) You may review copies at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 21, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–19199 Filed 10–2–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27010; Directorate 

Identifier 2006–NM–259–AD; Amendment 

39–15214; AD 2007–20–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 Airplanes and Model A310 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) 

that applies to all Airbus Model A300 

and A310 airplanes, and certain Model 

A300–600 series airplanes. That AD 

currently requires an inspection of the 

wing and center fuel tanks to determine 

if certain P-clips are installed and 

corrective action if necessary. That AD 

also requires an inspection of electrical 

bonding points of certain equipment in 

the center fuel tank for the presence of 

a blue coat and related investigative and 

corrective actions if necessary. That AD 

also requires installation of new 

bonding leads and electrical bonding 

points on certain equipment in the 

wing, center, and trim fuel tanks, as 

necessary. This new AD requires, for 

certain airplanes, installation of bonding 

on an additional bracket and 

modification of the fuel/defuel valves 

on the left-hand wing. This AD results 

from fuel system reviews conducted by 

the manufacturer. We are issuing this 

AD to ensure continuous electrical 

bonding protection of equipment in the 

wing, center, and trim fuel tanks and to 

prevent damage to wiring in the wing 

and center fuel tanks, due to failed Pclips used for retaining the wiring and 

pipes, which could result in a possible 

fuel ignition source in the fuel tanks. 

DATES: This AD becomes effective 

November 7, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 7, 2007. 

On August 29, 2006 (71 FR 42026, 

July 25, 2006), the Director of the 

Federal Register approved the 

incorporation by reference of certain 

other publications listed in the AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.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. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Tom 

Stafford, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1622; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov or in 

person at the Docket Operations office 

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

through Friday, except Federal holidays. 

The Docket Operations office (telephone 

(800) 647–5527) is located on the 

ground floor of the West Building at the 

DOT street address stated in the 

ADDRESSES section. 


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Federal Register / Vol. 72, No. 191 / Wednesday, October 3, 2007 / Rules and Regulations 56259 

Discussion 

The FAA issued a supplemental 

notice of proposed rulemaking (NPRM) 

to amend 14 CFR part 39 to include an 

AD that supersedes AD 2006–15–09, 

amendment 39–14689 (71 FR 42026, 

July 25, 2006). The existing AD applies 

to all Airbus Model A300, and Model 

A310 airplanes; and Model A300 B4–

600, B4–600R, and F4–600R series 

airplanes, and Model C4–605R Variant F 

airplanes (collectively called A300–600 

series airplanes). The supplemental 

NPRM was published in the Federal 

Register on June 20, 2007 (72 FR 33929). 

The supplemental NPRM proposed to 

require an inspection of the wing and 

center fuel tanks to determine if certain 

P-clips are installed and corrective 

action if necessary; an inspection of 

electrical bonding points of certain 

equipment in the center fuel tank for the 

presence of a blue coat and related 

investigative and corrective actions if 

necessary; and installation of new 

bonding leads and electrical bonding 

points on certain equipment in the 

wing, center, and trim fuel tanks, as 

necessary. That supplemental NPRM 

also proposed to require, for certain 

airplanes, installation of bonding on an 

additional bracket; and for certain other 

airplanes, modification of the fuel/ 

defuel valves on the left-hand wing. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Request To Revise Compliance Times 

and To Put New Actions in a Separate 

Rule 

Air Transport Association (ATA), on 

behalf of its member American Airlines 

(AA), is concerned with the 

administrative burden of the 

supplemental NPRM. The commenters 

point out that the supplemental NPRM 

contains multiple compliance periods 

for the required actions. The 

commenters believe that the multiple 

compliance periods should be 

consolidated into one compliance 

period. AA states that the scope of the 

existing AD along with the work added 

by the supplemental NPRM makes the 

proposed AD unwieldy to implement. 

AA states that considerable planning 

and procurement schedules must be 

accommodated for each additional AD, 

which disrupts planning that is already 

in place. The commenters state that the 

scope change described in the 

supplemental NPRM would have been 

more appropriately mandated as a 

separate rule. 

We do not agree that the compliance 

times should be consolidated into one 

compliance period. In developing the 

compliance time for this AD action, we 

considered not only the safety 

implications of the identified unsafe 

condition, but the average utilization 

rate of the affected fleet, the practical 

aspects of an orderly inspection or 

modification to the fleet during regular 

maintenance periods, the availability of 

required parts, and the time necessary 

for the rulemaking process. We also 

considered the compliance periods 

specified by the European Aviation 

Safety Agency (EASA) and the airplane 

manufacturer. We have determined that 

the proposed compliance times 

following the effective date of the AD 

are appropriate. We have not revised the 

AD in this regard. 

However, we do agree that the scope 

change in the supplemental NPRM is 

better mandated as a separate rule for 

reasons the commenters stated. Since 

we issued the supplemental NPRM, the 

EASA has revised its airworthiness 

directive to 2006–0325 R1, dated July 

25, 2007. (We cited the original issue of 

EASA airworthiness directive 2006–

0325, dated October 23, 2006, as the 

parallel airworthiness directive in the 

supplemental NPRM.) Revision 1 of the 

EASA airworthiness directive removes 

the procedures in Airbus Service 

Bulletin A300–28–6064 from its stated 

actions. Airbus Service Bulletin A300–

28–6064 includes procedures for Model 

A300–600 series airplanes. That service 

bulletin contains the scope change to 

which the commenters referred. R1 of 

the EASA airworthiness directive also 

removes Model A300–600 series 

airplanes from its applicability. As a 

result, we have revised the AD to do the 

following: 

• Remove paragraph (k) of the 

supplemental NPRM. That paragraph 

contains the scope change cited by the 

commenters. We have re-identified 

subsequent paragraphs accordingly. 

• Remove Model A300–600 series 

airplanes from the applicability. EASA 

is considering additional rulemaking 

regarding the unsafe condition for 

Model A300–600 series airplanes. Once 

the EASA airworthiness directive is 

approved, we will consider additional 

rulemaking for Model A300–600 series 

airplanes. 

• Remove Model A300–600 service 

bulletins from Table 1 of the 

supplemental NPRM. 

• Remove the costs information for 

Model A300–600 series airplanes from 

the Costs of Compliance section. 

• Revise the Related Information 

(paragraph (n) of the supplemental 

NPRM) to refer to Revision 1 of the 

EASA airworthiness directive. 

Conclusion 

We have carefully 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 have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

There are about 92 Model A300 and 

A310 airplanes of the affected design in 

the U.S. fleet. The following table 

provides the estimated costs, at an 

average labor rate of $80 per hour, for 

U.S. operators to comply with this AD. 

For some actions, the estimated work 

hours and cost of parts in the following 

table depend on the airplane 

configuration. 

ESTIMATED COSTS

Model Action Work hours Cost of parts Cost per 

airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

A300 airplanes .. Inspect wing and center fuel 

tanks for P-clips (required by 

AD 2006–15–09).

40 ..................... None ................ $3,200 .............. 29 $92,800. 

Install bonding leads/points in 

wing and center fuel tank (required by AD 2006–15–09).

Between 136 

and 155.

Between $3,800 

and $5,200.

Between 

$14,680 and 

$17,600.

29 Between 

$425,720 and 

$510,400. 

A310 airplanes .. Inspect wing and center fuel 

tanks for P-clips (required by 

AD 2006–15–09).

40 ..................... None ................ $3,200 .............. 63 $201,600. 


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56260 Federal Register / Vol. 72, No. 191 / Wednesday, October 3, 2007 / Rules and Regulations 

ESTIMATED COSTS—Continued 

Model Action Work hours Cost of parts Cost per 

airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Install bonding leads/points in 

wing and center fuel tank (required by AD 2006–15–09).

Between 248 

and 285.

Between $8,840 

and $9,190.

Between 

$28,680 and 

$31,990.

63 Between 

$1,806,840 

and 

$2,015,370. 

Inspect and install bonding 

leads/points in the trim fuel 

tank (required by AD 2006–

15–09).

Between 53 and 

61.

Between $50 

and $70.

Between $4,290 

and $4,950.

63 Between 

$270,270 and 

$311,850. 

Install bonding for slat track 11 

canister bracket (new action).

2 ....................... $30 ................... $190 ................. 63 $11,970. 

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 have 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 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14689 (71 

FR 42026, July 25, 2006) and by adding 

the following new airworthiness 

directive (AD): 

2007–20–04 Airbus: Amendment 39–15214. 

Docket No. FAA–2007–27010; 

Directorate Identifier 2006–NM–259–AD. 

Effective Date 

(a) This AD becomes effective November 7, 

2007. 

Affected ADs 

(b) This AD supersedes AD 2006–15–09. 

Applicability 

(c) This AD applies to all Model A300 and 

A310 airplanes, certificated in any category. 

Unsafe Condition 

(d) This AD results from fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to ensure continuous 

electrical bonding protection of equipment in 

the wing, center, and trim fuel tanks and to 

prevent damage to wiring in the wing and 

center fuel tanks, due to failed P-clips used 

for retaining the wiring and pipes, which 

could result in a possible fuel ignition source 

in the fuel tanks. 

Compliance 

(e) 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 the Requirements of AD 

2006–15–09 

Service Bulletin References 

(f) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Instructions of the service bulletins identified 

in Table 1 of this AD, as applicable. 

TABLE 1.—SERVICE BULLETIN REFERENCES

For Airbus— And the actions specified 

in—

Use Airbus Service 

Bulletin— Dated—

Model A300 airplanes .......... paragraph (g) of this AD ... A300–28–0081 .................. July 20, 2005. 

paragraph (h) of this AD ... A300–28–0079 .................. September 29, 2005; or Revision 01, dated June 6, 

2006. After the effective date of this AD, only Revision 01 may be used. 

Model A310 airplanes .......... paragraph (g) of this AD ... A310–28–2143 .................. July 20, 2005. 

paragraph (h) of this AD ... A310–28–2142 .................. August 26, 2005; or Revision 01, dated July 17, 2006. 

After the effective date of this AD, only Revision 01 

may be used. 


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Federal Register / Vol. 72, No. 191 / Wednesday, October 3, 2007 / Rules and Regulations 56261 

TABLE 1.—SERVICE BULLETIN REFERENCES—Continued 

For Airbus— And the actions specified 

in—

Use Airbus Service 

Bulletin— Dated—

paragraph (i) of this AD ..... A310–28–2153 .................. July 20, 2005. 

Inspection and Corrective Actions 

(g) Within 59 months after August 29, 2006 

(the effective date of AD 2006–15–09): Do a 

general visual inspection of the right and left 

wing fuel tanks and center fuel tank, if 

applicable, to determine if any NSA5516–

XXND– and NSA5516–XXNJ–type P-clips are 

installed for retaining wiring and pipes in 

any tank, and do all applicable corrective 

actions before further flight after the 

inspection, by accomplishing all the actions 

specified in the service bulletin. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

Installation of Bonding Leads and Points for 

Wing and Center Fuel Tanks 

(h) Within 59 months after August 29, 

2006: Do the actions specified in paragraphs 

(h)(1) and (h)(2) of this AD, by accomplishing 

all the actions specified in the service 

bulletin. 

(1) In the center fuel tank, if applicable, do 

a general visual inspection of the electrical 

bonding points of the equipment identified 

in the service bulletin for the presence of a 

blue coat, and do all related investigative and 

corrective actions before further flight after 

the inspection. 

(2) In the left and right wing fuel tanks and 

center fuel tank, if applicable, install bonding 

leads and electrical bonding points on the 

equipment identified in the service bulletin. 

Installation of Bonding Leads and Points for 

the Trim Fuel Tank 

(i) For Model A310 airplanes equipped 

with a trim fuel tank: Within 59 months after 

August 29, 2006, install a new bonding 

lead(s) on the water drain system of the trim 

fuel tank and install electrical bonding points 

on the equipment identified in the service 

bulletin in the trim fuel tank, by 

accomplishing all the actions specified in the 

service bulletin, as applicable. 

New Requirements of This AD 

Installation of Bonding for Slat Track 

Canister 11 Bracket 

(j) For all Model A310 airplanes on which 

the actions specified in Airbus Service 

Bulletin A310–28–2142, dated August 26, 

2005, have been done before the effective 

date of this AD: Within 50 months after the 

effective date of this AD, install bonding for 

the slat track canister 11 bracket, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310–

28–2142, Revision 01, dated July 17, 2006. 

Parts Installation 

(k) As of August 29, 2006, no person may 

install any NSA5516–XXND–or NSA5516–

XXNJ–type P-clip for retaining wiring and 

pipes in any wing, center, or trim fuel tank, 

on any airplane. 

Alternative Methods of Compliance (AMOCs) 

(l)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(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 appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(3) AMOCs approved previously in 

accordance with AD 2006–15–09 are 

approved as AMOCs for the corresponding 

provisions of this AD. 

Related Information 

(m) European Aviation Safety Agency 

airworthiness directive 2006–0325 R1, dated 

July 25, 2007, also addresses the subject of 

this AD. 

Material Incorporated by Reference 

(n) You must use the service information 

listed in Table 2 of this AD to perform the 

actions that are required by this AD, unless 

the AD specifies otherwise. 

TABLE 2.—ALL MATERIAL INCORPORATED BY REFERENCE

Airbus Service Bulletin— Revision level— Date—

A300–28–0079 ................................................................................................................................. Original ...................... September 29, 2005. 

A300–28–0079 ................................................................................................................................. 01 .............................. June 6, 2006. 

A300–28–0081 ................................................................................................................................. Original ...................... July 20, 2005. 

A310–28–2142 ................................................................................................................................. Original ...................... August 26, 2005. 

A310–28–2142 ................................................................................................................................. 01 .............................. July 17, 2006. 

A310–28–2143 ................................................................................................................................. Original ...................... July 20, 2005. 

A310–28–2153 ................................................................................................................................. Original ...................... July 20, 2005. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service bulletins listed in Table 3 of this 

AD in accordance with 5 U.S.C. 552(a) and 

1 CFR part 51. 

TABLE 3.—NEW MATERIAL INCORPORATED BY REFERENCE

Airbus Service Bulletin— Revision level— Date—

A300–28–0079 ................................................................................................................................. 01 .............................. June 6, 2006. 

A310–28–2142 ................................................................................................................................. 01 .............................. July 17, 2006. 


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56262 Federal Register / Vol. 72, No. 191 / Wednesday, October 3, 2007 / Rules and Regulations 

(2) On August 29, 2006 (71 FR 42026, July 

25, 2006), the Director of the Federal Register 

approved the incorporation by reference of 

the service bulletins listed in Table 4 of this 

AD. 

TABLE 4.—MATERIAL PREVIOUSLY

INCORPORATED BY REFERENCE

Airbus Service 

Bulletin— Dated—

A300–28–0079 ......... September 29, 2005. 

A300–28–0081 ......... July 20, 2005. 

A310–28–2142 ......... August 26, 2005. 

A310–28–2143 ......... July 20, 2005. 

A310–28–2153 ......... July 20, 2005. 

(3) Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, for a 

copy of this service information. You may 

review copies at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or 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/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on 

September 21, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–19206 Filed 10–2–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27015; Directorate 

Identifier 2006–NM–169–AD; Amendment 

39–15215; AD 2007–20–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318–111 and A318–112 Airplanes and 

Model A319, A320, and A321 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding two 

existing airworthiness directives (ADs). 

One AD applies to all Airbus Model 

A319 and A320 airplanes and currently 

requires repetitive ultrasonic 

inspections to detect fatigue cracking in 

the wing/fuselage joint cruciform 

fittings, and corrective actions if 

necessary. The other AD applies to all 

Airbus Model A319, A320, and A321 

airplanes and currently requires a 

revision to the Airworthiness 

Limitations section (ALS) of the 

Instructions for Continued 

Airworthiness (ICA). This new AD 

requires new revisions to the ALS of the 

ICA to incorporate service life limits for 

certain items and inspections to detect 

fatigue cracking, accidental damage, or 

corrosion in certain structures; and 

accomplishment of the repetitive 

ultrasonic inspections of the wing/ 

fuselage joint cruciform fittings in 

accordance with the revised ALS of the 

ICA. This AD also adds airplanes to the 

applicability. This AD results from 

issuance of new and more restrictive 

service life limits and structural 

inspections based on fatigue testing and 

in-service findings. We are issuing this 

AD to detect and correct fatigue 

cracking, accidental damage, or 

corrosion in principal structural 

elements and to prevent failure of 

certain life limited parts, which could 

result in reduced structural integrity of 

the airplane. 

DATES: This AD becomes effective 

November 7, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 7, 2007. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.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. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2141; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Operations office (telephone (800) 647–

5527) is located on the ground floor of 

the West Building at the DOT street 

address stated in the ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2004–03–06, amendment 

39–13450 (69 FR 5909, February 9, 

2004) and AD 2005–02–09, amendment 

39–13954 (70 FR 3871, January 27, 

2005). AD 2004–03–06 applies to all 

Airbus Model A319 and A320 airplanes, 

and AD 2005–02–09 applies to all 

Airbus Model A319, A320, and A321 

airplanes. That NPRM was published in 

the Federal Register on January 26, 

2007 (72 FR 3768). That NPRM 

proposed to require new revisions to the 

Airworthiness Limitations section (ALS) 

of the Instructions for Continued 

Airworthiness (ICA) to incorporate 

service life limits for certain items and 

inspections to detect fatigue cracking, 

accidental damage, or corrosion in 

certain structures; and accomplishment 

of the repetitive ultrasonic inspections 

of the wing/fuselage joint cruciform 

fittings in accordance with the revised 

ALS of the ICA. That NPRM also 

proposed to add airplanes to the 

applicability. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM. 

Support for the NPRM 

Airbus supports the NPRM. 

Northwest Airlines and United Airlines 

agree with the intent of the NPRM. 

Request To Incorporate Certain Service 

Information 

The Air Transport Association (ATA), 

on behalf of its member U.S. Airways, 

requests that we incorporate the 

following documents into this AD: 

Airbus Operator Information Telex 

(OIT) 999.0049/06, dated April 14, 2006; 

Airbus OIT 999.0055/06/CL, dated May 

4, 2006; and the Airbus A318/A319/ 

A320/A321 Scheduled Maintenance 

Data (SMD). The commenters further 

request that we revise this AD to allow 

operators to use later revisions of Airbus 

A318/A319/A320/A321 Airworthiness 

Limitation Items, Document AI/SE–M4/ 

95A.0252/96 (hereafter referred to as the 

‘‘Airbus ALI’’), as acceptable for 

compliance with the requirements of 

this AD. As justification for its request, 

US Airways states that Airbus will be 

revising the SMD and ALI on a regular 

basis. 

We agree to refer to Airbus ALI, Issue 

08, dated March 2006 (approved by the 

European Aviation Safety Agency 

(EASA) on January 4, 2007); and Issue 

09, dated November 2006 (approved by 

the EASA on May 21, 2007); as 

appropriate sources of service 

information for accomplishing the 

actions required by paragraph (i) of this 

AD. We have also revised paragraph (j) 


ebenthall on PRODPC61 with RULES