75878 Federal Register / Vol. 75, No. 234 / Tuesday, December 7, 2010 / Rules and Regulations 

TABLE 1—CREDIT SERVICE INFORMATION—Continued 

Document Date 

Boeing Service Bulletin DC9–28–212 ......................................................................................................................................... February 22, 2008. 

Boeing Service Bulletin MD90–28–010 ...................................................................................................................................... February 22, 2008. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), FAA, ATTN: Serj 

Harutunian, Aerospace Engineer, Propulsion 

Branch, ANM–140L, FAA, Los Angeles 

Aircraft Certification Office, 3960 Paramount 

Boulevard, Lakewood, California 90712– 

4137; telephone (562) 627–5254; fax (562) 

627–5210; has the authority to approve 

AMOCs for this AD, if requested using 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 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 

(k) 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. 

(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. 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Argo-Tech Service Bulletin 398000–28–2 ................................................................................................................ 1 December 2, 2008. 

Boeing Service Bulletin DC9–28–212 ...................................................................................................................... 1 June 16, 2009. 

Boeing Service Bulletin MD90–28–010 .................................................................................................................... 1 June 16, 2009. 

(2) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, 3855 Lakewood 

Boulevard, MC D800–0019, Long Beach, 

California 90846–0001; telephone 206–544– 

5000, extension 2; fax 206–766–5683; e-mail 

dse.boecom@boeing.com; Internet https:// 

www.myboeingfleet.com. For Argo-Tech 

service information identified in this AD, 

contact Argo-Tech Corporation, 23555 Euclid 

Avenue, Cleveland, Ohio 44117; telephone 

216–692–6000. 

(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 

November 24, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–30518 Filed 12–6–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0670; Directorate 

Identifier 2007–NM–339–AD; Amendment 

39–16526; AD 2010–24–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318–111 and A318–112 Airplanes and 

Model A319, A320, and A321 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: 

Damage to the lower lateral fittings of the 

80VU rack, typically elongated holes, 

migrated bushes [bushings], and/or missing 

bolts have been reported in-service. In 

addition damage to the lower central support 

fitting (including cracking) has been 

reported. 

In the worst case scenario a complete 

failure of the 80VU fittings in combination 

with a high load factor or strong vibration 

could lead to failure of the rack structure 

and/or computers or rupture/disconnection 

of the cable harnesses to one or more 

computers located in the 80VU. This rack 

contains computers for Flight Controls, 

Communication and Radio-navigation. These 

functions are duplicated across other racks 

but during critical phases of flight the 

multiple system failures/re-configuration 

may 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 

January 11, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 11, 2011. 

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: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2141; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (NPRM) to amend 

14 CFR part 39 to include an AD that 

would apply to the specified products. 


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That supplemental NPRM was 

published in the Federal Register on 

August 4, 2010 (75 FR 46873). That 

NPRM proposed to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Damage to the lower lateral fittings of the 

80VU rack, typically elongated holes, 

migrated bushes [bushings], and/or missing 

bolts have been reported in-service. In 

addition damage to the lower central support 

fitting (including cracking) has been 

reported. 

In the worst case scenario a complete 

failure of the 80VU fittings in combination 

with a high load factor or strong vibration 

could lead to failure of the rack structure 

and/or computers or rupture/disconnection 

of the cable harnesses to one or more 

computers located in the 80VU. This rack 

contains computers for Flight Controls, 

Communication and Radio-navigation. These 

functions are duplicated across other racks 

but during critical phases of flight the 

multiple system failures/re-configuration 

may constitute an unsafe condition. 

For the reasons described above, EASA AD 

2007–0276 was issued to require repetitive 

[detailed] inspection of the lower lateral 

80VU fittings for damage and [repetitive 

detailed] inspection of the lower central 

80VU support for damage and cracking, and 

the accomplishment of associated corrective 

actions, depending on findings. 

Since AD 2007–0276 was issued, Airbus 

introduced a new reinforced lower central 

support for the 80VU. 

This [EASA] AD has been revised to 

introduce the new reinforced lower central 

support as an optional terminating action to 

the repetitive inspections. 

* * * * * 

The associated corrective actions 

include repair or replacement of the 

lower lateral fittings and/or replacement 

of the lower central support. Modifying 

the 80VU lower lateral fittings (the 

modification includes replacing the 

80VU lower lateral fittings) eliminates 

the need for the repetitive inspection of 

the lower lateral fittings. Replacing the 

80VU lower central support (i.e., 

replacing the pyramid fitting on the 

80VU rack with a new, reinforced 

fitting) eliminates the need for the 

repetitive inspection of the lower 

central support. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Allow Credit for Actions 

Done per Previous Service Bulletin 

Lufthansa stated that paragraph (g) of 

the NPRM specifies that doing a 

modification in accordance with Airbus 

Service Bulletin A320–25–1557, 

Revision 02, dated November 5, 2008, 

terminates the inspections of the lateral 

fittings. The commenter stated this is 

not correct because any revision of the 

service bulletin terminates the 

inspections. 

We infer that Lufthansa requests that 

we revise paragraph (g) of the final rule 

to allow credit for actions done in 

accordance with previous issues of 

Airbus Service Bulletin A320–25–1557. 

We agree that previous issues are 

acceptable; however, it is not necessary 

to revise paragraph (g) of the final rule. 

We give credit for doing actions in 

accordance with previous revisions of 

the service information in paragraph (l) 

of the final rule. We have not changed 

this AD in this regard. 

Request To Defer Corrective Actions 

Lufthansa requested that we allow 

operators to defer doing the replacement 

specified in paragraph (j) of the NPRM. 

The commenter noted that Airbus 

Service Bulletin A320–53–1215, dated 

November 5, 2008, and EASA AD 2007– 

0276R1, dated March 18, 2010, both 

allow deferring the replacement. The 

commenter also noted that exhaustive 

data on cracks and crack growth are 

available on request. 

We disagree with the request to allow 

deferring the replacement required by 

paragraph (j) of the final rule. Our 

policy specifies the requirement to 

repair known cracks before further flight 

(though we might make exceptions to 

this policy in certain cases of unusual 

need). This policy is based on the fact 

that such damaged airplanes do not 

conform to the FAA-certificated type 

design and, therefore, are not airworthy 

until a properly approved repair is 

made. We consider the compliance 

times in this AD to be adequate to allow 

operators to acquire parts to have on 

hand in the event that a crack is 

detected during inspection. Therefore, 

we have determined that, due to the 

safety implications and consequences 

associated with such cracking, any 

subject 80VU rack lower central support 

that is found to be cracked must have 

associated corrective actions done 

before further flight. However, under the 

provisions of paragraph (m) of the final 

rule, we will consider requests for 

approval of an extension of the 

compliance time if sufficient data are 

submitted to substantiate that the new 

compliance time would provide an 

acceptable level of safety. We have not 

changed the AD in this regard. 

Request To Allow Alternate Actions in 

Lieu of the Replacement in Paragraph 

(j) of the NPRM 

Lufthansa further requested that we 

allow alternative actions other than 

doing a replacement in accordance with 

Airbus Service Bulletin A320–53–1215, 

dated November 5, 2008, as specified in 

paragraph (j) of the NPRM. The 

commenter stated that Airbus Service 

Bulletin A320–53–1215, dated 

November 5, 2008, and EASA AD 2007– 

0276R1, dated March 18, 2010, both 

specify repairing or replacing the 

pyramid fitting in accordance with 

Airbus Service Bulletin A320–25A1555, 

dated June 14, 2007; or Airbus Service 

Bulletin A320–25–1557, dated June 14, 

2007; as applicable. The commenter 

stated that allowing only the 

replacement in accordance with Airbus 

Service Bulletin A320–53–1215, dated 

November 5, 2008, is more restrictive to 

operators than necessary for continued 

flight safety. 

We disagree with the request to allow 

actions other than the replacement 

required by paragraph (j) of this AD. 

Doing the repair or replacement of the 

pyramid fitting in accordance with 

Airbus Service Bulletin A320–25A1555, 

dated June 14, 2007; or Airbus Service 

Bulletin A320–25–1557, dated June 14, 

2007; as applicable; would require also 

doing repetitive inspections. We can 

better ensure long-term continued 

operational safety by design changes to 

remove the source of the problem, rather 

than by repetitive inspections. Longterm inspections might not provide the 

degree of safety necessary for the 

transport airplane fleet. This 

determination, along with a better 

understanding of the human factors 

associated with numerous continual 

inspections, has led us to consider 

placing less emphasis on inspections 

and more emphasis on design 

improvements. The replacement 

required by paragraph (j) of the final 

rule is consistent with these conditions. 

However, under the provisions of 

paragraph (m) of the final rule, we will 

consider requests for alternative 

methods of compliance if sufficient data 

are submitted to substantiate that the 

alternative actions would provide an 

acceptable level of safety. We have not 

changed this AD in this regard. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

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 


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to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a Note within the AD. 

Costs of Compliance 

We estimate that this AD affects 678 

products of U.S. registry. We also 

estimate that takes about 82 work-hours 

per product to comply with the basic 

requirements of this AD. The average 

labor rate is $85 per work-hour. 

Required parts cost about $2,592 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of this AD 

to the U.S. operators to be $6,483,036, 

or $9,562 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 adding 

the following new AD: 

2010–24–07 Airbus: Amendment 39–16526. 

Docket No. FAA–2008–0670; Directorate 

Identifier 2007–NM–339–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective January 11, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A318– 

111, A318–112, A319–111, A319–112, A319– 

113, A319–114, A319–115, A319–131, A319– 

132, A319–133, A320–111, A320–211, A320– 

212, A320–214, A320–231, A320–232, A320– 

233, A321–111, A321–112, A321–131, A321– 

211, A321–212, A321–213, A321–231, and 

A321–232 airplanes, certificated in any 

category, all manufacturer serial numbers, 

except airplanes on which Airbus 

Modification 34804 has been embodied in 

production or on which Airbus Service 

Bulletins A320–25–1557 and A320–53–1215 

have been done in service. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 25: Equipment/Furnishings, 

and Code 53: Fuselage. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Damage to the lower lateral fittings of the 

80VU rack, typically elongated holes, 

migrated bushes [bushings], and/or missing 

bolts have been reported in-service. In 

addition damage to the lower central support 

fitting (including cracking) has been 

reported. 

In the worst case scenario a complete 

failure of the 80VU fittings in combination 

with a high load factor or strong vibration 

could lead to failure of the rack structure 

and/or computers or rupture/disconnection 

of the cable harnesses to one or more 

computers located in the 80VU. This rack 

contains computers for Flight Controls, 

Communication and Radio-navigation. These 

functions are duplicated across other racks 

but during critical phases of flight the 

multiple system failures/re-configuration 

may constitute an unsafe condition. 

* * * * * 

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. 

Repetitive Inspections of the 80V Rack 

Lower Lateral Fittings 

(g) Prior to the accumulation of 24,000 total 

flight cycles, or within 500 flight cycles after 

the effective date of this AD, whichever 

occurs later: Do a special detailed inspection 

of the 80VU rack lower lateral fittings for 

damage (e.g., broken fitting, missing bolts, 

migrated bushings, material burr, or rack in 

contact with the fitting) of the 80VU rack 

lower lateral fittings, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25A1555, 

Revision 02, dated November 5, 2008. Repeat 

the inspection thereafter at the interval 

specified in paragraph (g)(1) or (g)(2) of this 

AD, as applicable. Modifying the 80VU lower 

lateral fittings, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–25–1557, Revision 02, 

dated November 5, 2008, terminates the 

inspection requirements of this paragraph. 

(1) For airplanes on which the 80VU rack 

lower lateral fittings have not been replaced 

in accordance with the Airbus Mandatory 

Service Bulletin A320–25A1555: Repeat the 

inspection thereafter at intervals not to 

exceed 4,500 flight cycles. 

(2) For airplanes on which the 80VU rack 

lower lateral fittings have been replaced in 

accordance with Airbus Mandatory Service 

Bulletin A320–25A1555: Do the next 

inspection within 24,000 flight cycles after 

doing the replacement and repeat the 


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inspection thereafter at intervals not to 

exceed 4,500 flight cycles. 

(h) If any damage is found during any 

inspection required by paragraph (g) of this 

AD, do all applicable corrective actions 

(inspection and/or repair) in accordance with 

the Accomplishment Instructions and 

timeframes given in Airbus Mandatory 

Service Bulletin A320–25A1555, Revision 02, 

dated November 5, 2008. 

Repetitive Inspections of the 80V Rack 

Lower Central Support 

(i) Prior to the accumulation of 24,000 total 

flight cycles, or within 500 flight cycles after 

the effective date of this AD, whichever 

occurs later: Do a special detailed inspection 

of the 80VU rack lower central support for 

cracking, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25A1555, 

Revision 02, dated November 5, 2008. Repeat 

the inspection thereafter at the interval 

specified in paragraph (i)(1) or (i)(2) of this 

AD, as applicable. Replacing the pyramid 

fitting on the 80VU rack with a new, 

reinforced fitting, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1215, dated 

November 5, 2008, terminates the inspection 

requirements of this paragraph. 

(1) For airplanes on which the 80VU rack 

lower central support has not been repaired 

or replaced in accordance with Airbus 

Mandatory Service Bulletin A320–25A1555 

or Airbus Service Bulletin A320–25–1557: 

Repeat the inspection thereafter at the 

interval specified in paragraph (i)(1)(i) or 

(i)(1)(ii) of this AD, as applicable. 

(i) For airplanes on which the lower central 

support has accumulated 30,000 total flight 

cycles or more: At intervals not to exceed 500 

flight cycles. 

(ii) For airplanes on which the lower 

central support has accumulated less than 

30,000 total flight cycles: At intervals not to 

exceed 4,500 flight cycles, without exceeding 

30,750 total flight cycles on the support for 

the first repetitive inspection. 

(2) For airplanes on which the 80VU rack 

lower central support has been repaired or 

replaced in accordance with Airbus 

Mandatory Service Bulletin A320–25A1555 

or Airbus Service Bulletin A320–25–1557: Do 

the next inspection within 24,000 flight 

cycles after the repair or replacement and 

thereafter repeat the inspection at the interval 

specified in paragraph (i)(1)(i) or (i)(1)(ii) of 

this AD, as applicable. 

(j) If any crack is found during any 

inspection required by paragraph (i) of this 

AD, before further flight, replace the pyramid 

fitting on the 80VU rack with a new, 

reinforced fitting, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1215, dated 

November 5, 2008. Doing this replacement 

terminates the inspection requirements of 

paragraph (i) of this AD. 

Optional Terminating Action 

(k) Doing the actions specified in 

paragraphs (k)(1) and (k)(2) of this AD 

terminates the requirements of paragraphs (g) 

and (i) of this AD. 

(1) Replacing the pyramid fitting on the 

80VU rack with a new, reinforced fitting, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1215, dated November 5, 2008. 

(2) Modifying the 80VU lower lateral 

fittings, in accordance with Airbus Service 

Bulletin A320–25–1557, Revision 02, dated 

November 5, 2008. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(l) Actions done before the effective date of 

this AD in accordance with the service 

information identified in Table 1 of this AD 

are acceptable for compliance with the 

corresponding requirements of this AD. 

TABLE 1—PREVIOUS REVISIONS OF SERVICE INFORMATION

Service information Revision level Date 

Airbus Mandatory Service Bulletin A320–25A1555 ......................................................... 01 ......................................... February 18, 2008. 

Airbus Service Bulletin A320–25A1555 ........................................................................... Original ................................ June 14, 2007. 

Airbus Service Bulletin A320–25–1557 ............................................................................ Original ................................ June 14, 2007. 

Airbus Service Bulletin A320–25–1557 ............................................................................ 01 ......................................... February 7, 2008. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

(1) Although the MCAI or service 

information allows further flight after cracks 

are found during compliance with the 

required action, paragraph (j) of this AD 

requires that you do a corrective action 

before further flight. 

(2) Although the MCAI specifies doing a 

repair or replacement and repetitive 

inspections after the repair or replacement is 

done if cracking is found in the 80VU rack 

lower central support, paragraph (j) of this 

AD requires that you perform a replacement, 

which eliminates the need for further 

repetitive inspections of the part. 

Other FAA AD Provisions 

(m) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, ANM–116, 

International Branch, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Tim Dulin, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2141; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: A Federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave., SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(n) Refer to MCAI EASA Airworthiness 

Directive 2007–0276R1, dated March 18, 

2010, (corrected April 12, 2010), and the 

service information identified in Table 2 of 

this AD, for related information. 

TABLE 2—RELATED SERVICE INFORMATION

Service information Revision level Date 

Airbus Mandatory Service Bulletin A320–25A1555 ......................................................... 02 ......................................... November 5, 2008. 


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TABLE 2—RELATED SERVICE INFORMATION—Continued 

Service information Revision level Date 

Airbus Service Bulletin A320–25–1557 ............................................................................ 02 ......................................... November 5, 2008. 

Airbus Service Bulletin A320–53–1215 ............................................................................ Original ................................ November 5, 2008. 

Material Incorporated by Reference 

(o) You must use the service information 

specified in paragraphs (o)(1) and (o)(2) of 

this AD, as applicable, unless the AD 

specifies otherwise. 

(1) For the actions required by this AD: 

Airbus Mandatory Service Bulletin A320– 

25A1555, excluding Appendix 1, Revision 

02, dated November 5, 2008; and Airbus 

Service Bulletin A320–53–1215, dated 

November 5, 2008. 

(2) For the optional actions specified by 

this AD: Airbus Service Bulletin A320–25– 

1557, Revision 02, dated November 5, 2008; 

and Airbus Service Bulletin A320–53–1215, 

dated November 5, 2008. 

(3) 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. 

(4) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; e-mail 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.com. 

(5) 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. 

(6) 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 

November 15, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–29457 Filed 12–6–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0942; Directorate 

Identifier 2010–CE–049–AD; Amendment 

39–16535; AD 2010–25–02] 

RIN 2120–AA64 

Airworthiness Directives; British 

Aerospace Regional Aircraft Models 

Jetstream Series 3101 and Jetstream 

Model 3201 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) 

issued 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: 

As a result of the fatigue-testing 

programme on the Jetstream fatigue test 

specimen, it has been identified that failure 

of the undercarriage jack mounting shaft 

assembly can occur. 

This condition, if not corrected, could lead 

to a Main Landing Gear (MLG) collapse on 

the ground or during landing and 

consequently damage to the aeroplane or 

injury to the occupants. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

January 11, 2011. 

On January 11, 2011, the Director of 

the Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

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 service information identified in 

this AD, contact BAE Systems 

(Operations) Ltd, Customer Information 

Department, Prestwick International 

Airport, Ayrshire, KA9 2RW, Scotland, 

United Kingdom; telephone +44 1292 

675207, fax: +44 1292 675704; e-mail: 

RApublications@baesystems.com. You 

may review copies of the referenced 

service information at the FAA, Small 

Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call 816–329–4148. 

FOR FURTHER INFORMATION CONTACT: 

Taylor Martin, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4138; fax: (816) 329–4090; e-mail: 

taylor.martin@faa.gov. 

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 September 27, 2010 (75 FR 

59170). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

As a result of the fatigue-testing 

programme on the Jetstream fatigue test 

specimen, it has been identified that failure 

of the undercarriage jack mounting shaft 

assembly can occur. 

This condition, if not corrected, could lead 

to a Main Landing Gear (MLG) collapse on 

the ground or during landing and 

consequently damage to the aeroplane or 

injury to the occupants. 

BAE SYSTEMS have now defined safe life 

limits for these components. 

For the reasons described above, this AD 

requires the application of safe life limits to 

these components. 

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. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 


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