Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 46339 

The AMOC approval letter must specifically 

reference this AD. 

(2) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(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. 

(4) Special Flight Permits: We are 

permitting special flight permits provided 

that the airplane is unpressurized during 

flight. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency (EASA) Emergency 

Airworthiness Directive 2009–0159–E, dated 

July 20, 2009; and PPG Aerospace Service 

Bulletin NP–158862–001, dated July 8, 2009; 

for related information. 

Material Incorporated by Reference 

(i) You must use PPG Aerospace Service 

Bulletin NP–158862–001, dated July 8, 2009, 

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 PPG Aerospace, 12780 San 

Fernando Road, Sylmar, California 91342; 

telephone 818–362–6711; fax 818–362–0603; 

Internet http://corporateportal.ppg.com/na/ 

aerospace. 

(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 or 425–227–1152. 

(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 August 

26, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–21312 Filed 9–8–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0522; Directorate 

Identifier 2008–NM–127–AD; Amendment 

39–16010; AD 2009–18–14] 

RIN 2120–AA64 

Airworthiness Directives; 328 Support 

Services GmbH Dornier Model 328–100 

and –300 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

* * * A number of * * * rudder spring 

tab lever assemblies [of the rudder] were 

found cracked. 

This condition, if not corrected, could lead 

to failure of the rudder flight control system 

and consequent loss of control of the aircraft. 

* * * 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

October 14, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 14, 2009. 

On June 9, 2004 (69 FR 24953, May 

5, 2004), the Director of the Federal 

Register approved the incorporation by 

reference of certain other publications 

listed in this AD. 

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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2125; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 9, 2009 (74 FR 27257), 

and proposed to supersede AD 2004– 

09–16, Amendment 39–13605 (69 FR 

24953, May 5, 2004). (A correction of 

that AD was published in the Federal 

Register on May 12, 2004 (69 FR 

26434)). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

On 14 March 2002, an incident occurred 

with a Dornier 328–100 where the captain 

reported that the rudder was unresponsive. 

The aircraft landed without any further 

difficulties. A visual inspection of the rudder 

assembly was carried out and the spring tab 

assembly was found to be cracked and 

partially missing. During subsequent 

inspections of other aircraft, a number of 

additional rudder spring tab lever assemblies 

were found cracked. 

This condition, if not corrected, could lead 

to failure of the rudder flight control system 

and consequent loss of control of the aircraft. 

To address and correct this unsafe condition, 

LBA (Luftfahrt-Bundesamt) issued AD 2003– 

383 and 2003–384 [which correspond to FAA 

AD 2004–09–16] for the Dornier 328–100 and 

328–300 respectively, to require the initial 

and repetitive inspection of the rudder spring 

tab lever assembly and, in case cracks were 

found, the replacement of the rudder spring 

tab lever assembly with a serviceable unit. 

The current TC (type certificate) holder of 

this type design, 328 Support Services 

GmbH, has recently published Alert Service 

Bulletin ASB–328–27–036, Revision 2, which 

reduces the inspection interval to A-check 

[400 FH] (400 flight hours). In addition, 

Service Bulletin SB–328–27–459 was revised 

to change the compliance status from 

‘optional’ to ‘mandatory’ and instructs 

operators to replace the rudder spring tab 

lever assembly with an improved unit P/N 

(part number) 001A272A4020–004, ending 

the need for the repetitive inspections. 

For the reasons described above, this EASA 

AD retains the repetitive inspection 

requirements of LBA AD 2003–383, which is 

superseded, expands the applicability to all 

serial numbers, reduces the inspection 

interval to 400 [flight hours], and requires the 

replacement of the rudder spring tab lever 

assembly with an improved unit P/N 

001A272A4020–004, as specified in SB–328– 

27–459. 

The material used for the rudder 

spring tab lever assemblies on Model 

328–100 airplanes differs from the 

material used for the rudder spring tab 

lever assemblies on Model 328–300 

airplanes. Therefore, Model 328–300 

airplanes are not affected by the new 

requirements in this AD. You may 

obtain further information by examining 

the MCAI in the AD docket. 


jlentini on DSKJ8SOYB1PROD with RULES
46340 Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Explanation of Change to Final Rule 

This AD does not require reporting 

crack findings to the manufacturer. 

Therefore, we have removed paragraph 

(m)(3) of the proposed AD because the 

reporting requirements information in 

that paragraph is not necessary. 

Conclusion 

We reviewed the available data, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We determined that this change will not 

increase the economic burden on any 

operator or increase the scope of the AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a Note within the AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD affects about 112 

products of U.S. registry. 

The actions that are required by AD 

2004–09–16 and retained in this AD 

affect 112 products of U.S. registry and 

take 1 work-hour per product, at an 

average labor rate of $80 per work-hour. 

Based on these figures, the estimated 

cost of the currently required actions is 

$8,960, or $80 per product, per 

inspection cycle. 

We estimate that it will take 3 workhours per product to comply with the 

new basic requirements of this AD and 

it will affect 16 products of U.S. registry. 

The average labor rate is $80 per workhour. Required parts will cost about 

$12,861 per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these costs. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of the 

AD on U.S. operators to be $209,616, or 

$13,101 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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 

removing Amendment 39–13605 (69 FR 

24953, May 5, 2004), and adding the 

following new AD: 

2009–18–14 328 Support Services GmbH 

(Formerly, AvCraft Aerospace GmbH, 

formerly Fairchild Dornier GmbH, 

formerly Dornier Luftfahrt GmbH): 

Amendment 39–16010. Docket No. 

FAA–2009–0522; Directorate Identifier 

2008–NM–127–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 14, 2009. 

Affected ADs 

(b) This AD supersedes AD 2004–09–16, 

Amendment 39–13605. 

Applicability 

(c) This AD applies to 328 Support 

Services GmbH Dornier Model 328–100 

airplanes on which a rudder spring tab lever 

assembly having part number 

001A272A4020–002 is installed, and all 

Model 328–300 airplanes. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

On 14 March 2002, an incident occurred 

with a Dornier 328–100 where the captain 

reported that the rudder was unresponsive. 

The aircraft landed without any further 

difficulties. A visual inspection of the rudder 

assembly was carried out and the spring tab 

assembly was found to be cracked and 

partially missing. During subsequent 

inspections of other aircraft, a number of 

additional rudder spring tab lever assemblies 

were found cracked. 

This condition, if not corrected, could lead 

to failure of the rudder flight control system 

and consequent loss of control of the aircraft. 

To address and correct this unsafe condition, 

LBA (Luftfahrt-Bundesamt) issued AD 2003– 

383 and 2003–384 [which correspond to FAA 


jlentini on DSKJ8SOYB1PROD with RULES
Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 46341 

AD 2004–09–16] for the Dornier 328–100 and 

328–300 respectively, to require the initial 

and repetitive inspection of the rudder spring 

tab lever assembly and, in case cracks were 

found, the replacement of the rudder spring 

tab lever assembly with a serviceable unit. 

The current TC (type certificate) holder of 

this type design, 328 Support Services 

GmbH, has recently published Alert Service 

Bulletin ASB–328–27–036, Revision 2, which 

reduces the inspection interval to A-check 

[400 FH] (400 flight hours). In addition, 

Service Bulletin SB–328–27–459 was revised 

to change the compliance status from 

‘optional’ to ‘mandatory’ and instructs 

operators to replace the rudder spring tab 

lever assembly with an improved unit P/N 

(part number) 001A272A4020–004, ending 

the need for the repetitive inspections. 

For the reasons described above, this EASA 

AD retains the repetitive inspection 

requirements of LBA AD 2003–383, which is 

superseded, expands the applicability to all 

serial numbers, reduces the inspection 

interval to 400 [flight hours], and requires the 

replacement of the rudder spring tab lever 

assembly with an improved unit P/N 

001A272A4020–004, as specified in SB–328– 

27–459. 

Compliance 

(f) Required as indicated, unless 

accomplished previously. 

Restatement of Requirements of AD 2004– 

09–16, Including Repetitive Inspections With 

Reduced Intervals for Model 328–100 

Airplanes 

(g) For all airplanes: Within 400 flight 

hours or 2 months after June 9, 2004 (the 

effective date of AD 2004–09–16), whichever 

is first; do detailed and eddy current 

inspections for cracking of the bearing lugs 

of the rudder spring tab lever assembly by 

doing all the actions per Paragraphs 2.A., 

2.B., and 2.D. of the Accomplishment 

Instructions of Dornier Alert Service Bulletin 

ASB–328–27–036 (for Model 328–100 

airplanes), dated February 12, 2003, or 

Revision 3, dated February 8, 2008; or 

Dornier Alert Service Bulletin ASB–328J–27– 

013 (for Model 328–300 airplanes), dated 

February 12, 2003; as applicable. 

Note 1: For the purposes of this AD, a 

detailed inspection is defined as: ‘‘An 

intensive visual examination of a specific 

structural area, system, installation, or 

assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at intensity deemed appropriate by 

the inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’ 

(1) For Model 328–100 airplanes: If no 

cracking is found during any inspection 

required by paragraph (g) of this AD, do the 

next inspection within 400 flight hours after 

doing the last inspection, or within 400 flight 

hours after the effective date of this AD, 

whichever occurs later; and repeat the 

inspection thereafter at intervals not to 

exceed 400 flight hours. Repeat the 

inspections until the replacement required by 

paragraph (k) of this AD has been done. 

(2) For Model 328–300 airplanes: If no 

cracking is found during any inspection 

required by paragraph (g) of this AD, repeat 

the inspections thereafter at intervals not to 

exceed 24 months. 

Corrective Action 

(h) For all airplanes: If any cracking is 

found during any inspection required by 

paragraph (g) of this AD, do the applicable 

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

of this AD. 

(1) For Model 328–100 airplanes: Before 

further flight, do the replacement required by 

paragraph (k) of this AD, or replace the 

spring tab lever assembly with a new 

assembly by doing all the actions per 

Paragraph 2.C. of the Accomplishment 

Instructions of Dornier Alert Service Bulletin 

ASB–328–27–036, dated February 12, 2003; 

or Revision 3, dated February 8, 2008. 

(2) For Model 328–300 airplanes: Before 

further flight, replace the spring tab lever 

assembly with a new assembly by doing all 

the actions per Paragraph 2.C. of the 

Accomplishment Instructions of Dornier 

Alert Service Bulletin ASB–328J–27–013, 

dated February 12, 2003. Repeat the 

inspections required by paragraph (g) of this 

AD thereafter at intervals not to exceed 24 

months. 

Note 2: For Model 328–300 airplanes: 

There is no terminating action available for 

the repetitive inspections required by this 

AD. 

(i) Dornier Alert Service Bulletins ASB– 

328–27–036, dated February 12, 2003, and 

Revision 3, dated February 8, 2008; and 

ASB–328J–27–013, dated February 12, 2003; 

recommend reporting crack findings and 

returning damaged lever assemblies to the 

manufacturer, but this AD does not contain 

such requirements. 

New Requirements of This AD: Actions and 

Compliance 

(j) For Model 328–100 airplanes: As of the 

effective date of this AD, Dornier Alert 

Service Bulletin ASB–328–27–036, Revision 

3, dated February 8, 2008, must be used for 

accomplishing the inspections and corrective 

actions required by paragraphs (g) and (h) of 

this AD. 

(k) For Model 328–100 airplanes: Within 6 

months after the effective date of this AD, 

replace any rudder spring tab lever assembly 

having P/N 001A272A4020–002 with an 

improved unit having P/N 001A272A4020– 

004, in accordance with the Accomplishment 

Instructions of Dornier Service Bulletin SB– 

328–27–459, Revision 2, dated February 8, 

2008. Accomplishment of the replacement 

required by this paragraph terminates the 

repetitive inspections required by paragraph 

(g)(1) of this AD. 

(l) Actions done before the effective date of 

this AD in accordance with Dornier Service 

Bulletin SB–328–27–459, dated May 3, 2004; 

or Revision 1, dated January 24, 2008; are 

acceptable for compliance with the 

corresponding requirements of this AD for 

Model 328–100 airplanes. Actions done 

before the effective date of this AD in 

accordance with Dornier Alert Service 

Bulletin ASB–328–27–036, Revision 1, dated 

May 7, 2004; or Revision 2, dated January 24, 

2008; are acceptable for compliance with the 

corresponding requirements of this AD for 

Model 328–300 airplanes. 

FAA AD Differences 

Note 3: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(m) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; 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. 

(2) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

Related Information 

(n) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2008– 

0107, dated June 23, 2008; German 

Airworthiness Directive 2003–384, dated 

November 13, 2003; and the service 

information contained in Table 1 of this AD, 

for related information. 

TABLE 1—RELATED SERVICE INFORMATION

Document Revision Date 

Dornier Alert Service Bulletin ASB–328–27–036 .............. 3 ......................................................................................... February 8, 2008. 

Dornier Alert Service Bulletin ASB–328J–27–013 ............ Original ............................................................................... February 12, 2003. 

Dornier Service Bulletin SB–328–27–459 ......................... 2 ......................................................................................... February 8, 2008. 


jlentini on DSKJ8SOYB1PROD with RULES
46342 Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 

Material Incorporated by Reference 

(o) You must use the applicable service 

information contained in Table 2 of this AD 

to do the actions required by this AD, unless 

the AD specifies otherwise. (The issue date 

of Dornier Alert Service Bulletin ASB–328– 

27–036, Revision 3, dated February 8, 2008; 

and Dornier Service Bulletin SB–328–27– 

459, Revision 2, dated February 8, 2008; is 

specified only on the odd-numbered pages of 

these documents.) 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Dornier Alert Service Bulletin ASB–328–27–036 .............. 3 ......................................................................................... February 8, 2008. 

Dornier Alert Service Bulletin ASB–328J–27–013 ............ Original ............................................................................... February 12, 2003. 

Dornier Service Bulletin SB–328–27–459 ......................... 2 ......................................................................................... February 8, 2008. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Dornier Alert Service Bulletin ASB–328–27– 

036, Revision 3, dated February 8, 2008; and 

Dornier Service Bulletin SB–328–27–459, 

Revision 2, dated February 8, 2008; under 5 

U.S.C. 552(a) and 1 CFR part 51. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of the Dornier Alert Service 

Bulletin ASB–328J–27–013, dated February 

12, 2003, on June 9, 2004 (69 FR 24953, May 

5, 2004). 

(3) For service information identified in 

this AD, contact 328 Support Services GmbH, 

Global Support Center, P.O. Box 1252, D– 

82231 Wessling, Federal Republic of 

Germany; telephone +49 8153 88111 6666; 

fax +49 8153 88111 6565; e-mail 

gsc.op@328support.de; Internet http:// 

www.328support.de. 

(4) 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 or 425–227–1152. 

(5) 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 August 

24, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–21035 Filed 9–8–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0465; Directorate 

Identifier 2007–NM–244–AD; Amendment 

39–16012; AD 2009–18–16] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310–203, –204, –221, –222, –304, 

–322, –324, and –325 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France issued AD F–2005–078 [which 

corresponds to FAA AD 2006–02–06] to 

require the modification (Airbus 

modification 13023), defined in Airbus SB 

[service bulletin] A310–53–2124, to increase 

the service life of junctions of center box 

upper frame bases to upper fuselage arches. 

This structural modification falls within the 

scope of the work related to the extension of 

the service life of A310 aircraft and 

widespread fatigue damage evaluations. 

The threshold timescales for 

accomplishment of the tasks as defined in SB 

A310–53–2124 were refined and reduced. 

* * * 

* * * * * 

The unsafe condition is fatigue cracking 

of the frame foot run-outs, which could 

lead to rupture of the frame foot and 

cracking in adjacent frames and skin, 

and which could result in reduced 

structural integrity of the fuselage. We 

are issuing this AD to require actions to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective 

October 14, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 14, 2009. 

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: Tom 

Stafford, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 227–1622; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 2, 2009 (74 FR 26312), 

and proposed to supersede AD 2006– 

02–06, Amendment 39–14458 (71 FR 

3214, January 20, 2006). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France issued AD F–2005–078 [which 

corresponds to FAA AD 2006–02–06, 

Amendment 39–14458, 71 FR 3214, January 

20, 2006] to require the modification (Airbus 

modification 13023), defined in Airbus SB 

[service bulletin] A310–53–2124, to increase 

the service life of junctions of center box 

upper frame bases to upper fuselage arches. 

This structural modification falls within the 

scope of the work related to the extension of 

the service life of A310 aircraft and 

widespread fatigue damage evaluations. 

The threshold timescales for 

accomplishment of the tasks as defined in SB 

A310–53–2124 were refined and reduced. 

Consequently, EASA issued AD 2007–0238 

to require compliance with Revision 1 of SB 

A310–53–2124 at the reduced compliance 

times, superseding (the requirements of) 

DGAC France AD F–2005–078. Subsequently, 


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