Federal Register / Vol. 75, No. 47 / Thursday, March 11, 2010 / Rules and Regulations 11435 

Actions Compliance Procedures 

(1) Inspect the installation of the stand-off hardware between the heater fuel line and heater 

over-temperature sensor wires for minimum 

clearance.

Within the next 50 hours time-in-service (TIS) 

after April 15, 2010 (the effective date of 

this AD) or within the next 12 months after 

April 15, 2010 (the effective date of this 

AD), whichever occurs first.

Follow Hawker Beechcraft Mandatory Service 

Bulletin SB 32–3898, dated November 

2008. 

(2) If, during the inspection required in paragraph (f)(1) of this AD, the stand-off hardware is not installed or it does not maintain 

the minimum clearance, install stand-off hardware as specified in the service information.

Before further flight after the inspection where 

the missing stand-off hardware and/or inadequate clearance was found.

Follow Hawker Beechcraft Mandatory Service 

Bulletin SB 32–3898, dated November 

2008. 

(3) Inspect the brake reservoir line and the fuel 

heater power wire for damage.

Within the next 50 hours TIS after April 15, 

2010 (the effective date of this AD) or within the next 12 months after April 15, 2010 

(the effective date of this AD), whichever 

occurs first.

Follow Hawker Beechcraft Mandatory Service 

Bulletin SB 32–3898, dated November 

2008. 

(4) If, during the inspection required in paragraph (f)(3) of this AD, damage is found, repair or replace damaged tubing and/or wiring 

found.

Before further flight after the inspection where 

damaged tubing and/or wiring was found.

Follow Hawker Beechcraft Mandatory Service 

Bulletin SB 32–3898, dated November 

2008. 

(5) Inspect the installation of the stand-off hardware between the brake reservoir line and 

the fuel heater power wire for minimum clearance.

Within the next 50 hours TIS after April 15, 

2010 (the effective date of this AD) or within the next 12 months after April 15, 2010 

(the effective date of this AD), whichever 

occurs first.

Follow Hawker Beechcraft Mandatory Service 

Bulletin SB 32–3898, dated November 

2008. 

(6) If, during the inspection required in paragraph (f)(5) of this AD, the stand-off hardware is not installed or it does not maintain 

the minimum clearance, install stand-off hardware as specified in the service information.

Before further flight after the inspection where 

the missing stand-off hardware and/or inadequate clearance was found.

Follow Hawker Beechcraft Mandatory Service 

Bulletin SB 32–3898, dated November 

2008. 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, Wichita Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: Kevin 

Schwemmer, Aerospace Engineer, FAA 

Wichita Aircraft Certification Office, 1801 

Airport Road, Room 100, Wichita, Kansas 

67209; telephone: (316) 946–4174; fax: (316) 

946–4107. 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. 

Material Incorporated by Reference 

(h) You must use Hawker Beechcraft 

Mandatory Service Bulletin SB 32–3898, 

dated November 2008, 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 Hawker Beechcraft 

Corporation, P.O. Box 85, Wichita, Kansas 

67201–0085; telephone: 1 (800) 429–5372 or 

(316) 676–3140; fax: (316) 676–3340; 

Internet: http://www.hawkerbeechcraft.com. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri, on March 

2, 2010. 

Sandra J. Campbell, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–5024 Filed 3–10–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0993; Directorate 

Identifier 2009–NM–089–AD; Amendment 

39–16229; AD 2010–06–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–2C, B4–103, and B4–203 

Airplanes; and Model A300 B4–601, 

B4–603, B4–620, B4–622, B4–605R, 

and B4–622R 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: 

One A300–600 aeroplane operator reported 

that, during a routine inspection, the Right 

Hand frame 40 forward fitting between 

stringer 32 and stringer 33 was found 

cracked. The subject aeroplane had 

previously been modified in accordance with 

Airbus SB A300–57–6053 (Airbus 

Modification 10453). 

This condition, if not corrected, could 

result in a deterioration of the structural 

integrity of the frame. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective April 

15, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 15, 2010. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 


jlentini on DSKJ8SOYB1PROD with RULES
11436 Federal Register / Vol. 75, No. 47 / Thursday, March 11, 2010 / Rules and Regulations 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

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 October 28, 2009 (74 FR 

55485). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

One A300–600 aeroplane operator reported 

that, during a routine inspection, the Right 

Hand frame 40 forward fitting between 

stringer 32 and stringer 33 was found 

cracked. The subject aeroplane had 

previously been modified in accordance with 

Airbus SB A300–57–6053 (Airbus 

Modification 10453). 

This condition, if not corrected, could 

result in a deterioration of the structural 

integrity of the frame. 

As no fatigue maintenance tasks 

(Inspection SB or Airworthiness Limitation 

Item) presently exist to inspect the affected 

area for aeroplanes having incorporated 

Airbus Modification 10453 preventively 

(without preliminary crack finding), Airbus 

has developed a new inspection [for 

cracking, and repair if necessary] to ensure 

structural integrity of the concerned area of 

frame 40. 

* * * * * 

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 comment received. 

Request To Increase Work Hours 

FedEx Express states that it has 

determined that the inspection 

thresholds in the NPRM allow sufficient 

time to accomplish the proposed 

inspection during a scheduled 

maintenance check. FedEx Express adds 

that the number of work-hours and 

elapsed time necessary to accomplish 

the proposed inspections will not 

impact the overall span-time of its 

planned scheduled maintenance check, 

unless cracks are found. FedEx Express 

notes that if cracks are found, significant 

downtime of approximately 42 hours 

will be required to accomplish the 

corrective action. FedEx Express adds 

that it has already accomplished the 

inspections on five airplanes with no 

crack findings. 

From these statements, we infer that 

FedEx Express is requesting that we 

revise the AD to include the work-hours 

necessary to repair any crack findings. 

We do not agree. The economic analysis 

of the AD is limited only to the cost of 

actions actually required by the rule. It 

does not consider the costs of ‘‘oncondition’’ actions (that is, actions 

needed to correct an unsafe condition 

such as cracking), because, regardless of 

AD direction, those actions would be 

required to correct an unsafe condition 

identified in an airplane and ensure 

operation of that airplane in an 

airworthy condition, as required by the 

Federal Aviation Regulations. We have 

not changed the AD in this regard. 

Explanation of Additional Note in the 

Final Rule 

We have included a new Note 2 in 

this AD (and renumbered subsequent 

notes accordingly) to provide 

clarification that a repair is considered 

any modification that restores the 

original strength of the cracked part. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We also 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. 

Explanation of Change to Costs of 

Compliance 

Since issuance of the original NPRM, 

we have increased the labor rate used in 

the Costs of Compliance from $80 per 

work hour to $85 per work hour. The 

Costs of Compliance information, 

below, reflects this increase in the 

specified hourly labor rate. 

Costs of Compliance 

We estimate that this AD will affect 

153 products of U.S. registry. We also 

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

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $39,015, or $255 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 


jlentini on DSKJ8SOYB1PROD with RULES
Federal Register / Vol. 75, No. 47 / Thursday, March 11, 2010 / Rules and Regulations 11437 

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: 

2010–06–05 Airbus: Amendment 39–16229. 

Docket No. FAA–2009–0993; Directorate 

Identifier 2009–NM–089–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 15, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus airplanes, 

certificated in any category, as identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Model A300 B4–2C, B4–103, and B4– 

203 airplanes, all serial numbers, modified 

preventively in service (without preliminary 

crack findings) in accordance with Airbus 

Service Bulletin A300–53–0297 (Airbus 

Modification 10453). 

(2) Model A300 B4–601, B4–603, B4–605R, 

B4–620, B4–622, and B4–622R airplanes, all 

serial numbers, modified preventively in 

service (without preliminary crack findings) 

in accordance with Airbus Service Bulletin 

A300–57–6053 (Airbus Modification 10453). 

Note 1: For airplanes on which Airbus 

Service Bulletin A300–53–0297 or A300–57– 

6053 (Airbus Modification 10453), as 

applicable, has been incorporated as a 

corrective action (repair following crack 

finding), no action is required by this AD. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

‘‘One A300–600 aeroplane operator 

reported that, during a routine inspection, 

the Right Hand frame 40 forward fitting 

between stringer 32 and stringer 33 was 

found cracked. The subject aeroplane had 

previously been modified in accordance with 

Airbus SB A300–57–6053 (Airbus 

Modification 10453). 

‘‘This condition, if not corrected, could 

result in a deterioration of the structural 

integrity of the frame. 

‘‘As no fatigue maintenance tasks 

(Inspection SB or Airworthiness Limitation 

Item) presently exist to inspect the affected 

area for aeroplanes having incorporated 

Airbus Modification 10453 preventively 

(without preliminary crack finding), Airbus 

has developed a new inspection [for 

cracking, and repair if necessary] to ensure 

structural integrity of the concerned area of 

frame 40.’’ 

* * * * * 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) At the applicable time specified in 

Table 1 of this AD: Do a one-time detailed 

visual inspection of the forward fitting at 

frame 40 on both sides of the airplane, in 

accordance with Airbus Mandatory Service 

Bulletin A300–57A6108 (for Model A300 B4– 

601, B4–603, B4–605R, B4–620, B4–622, and 

B4–622R airplanes) or A300–53A0387 (for 

Model A300 B4–2C, B4–103, and B4–203 

airplanes), both including Appendices 01 

and 02, both dated September 12, 2008. 

TABLE 1—COMPLIANCE TIMES

Airplane models/configuration Compliance time 

A300 B4–2C and B4–103 airplanes on which Airbus 

Service Bulletin A300–53–0297 was done prior to the 

accumulation of 9,000 total flight cycles.

Prior to the accumulation of 18,000 total flight cycles, or within 3 months after the effective date of this AD, whichever occurs later. 

A300 B4–2C and B4–103 airplanes on which Airbus 

Service Bulletin A300–53–0297 was done on or after 

the accumulation of 9,000 total flight cycles.

Within 5,500 flight cycles after accomplishment of Airbus Service Bulletin A300–53– 

0297, or within 6 months after the effective date of this AD, whichever occurs later; 

except, for airplanes that, as of the effective date of this AD, have accumulated 

11,000 flight cycles or more since accomplishment of Airbus Service Bulletin 

A300–53–0297, within 3 months after the effective date of this AD. 

A300 B4–203 airplanes on which Airbus Service Bulletin 

A300–53–0297 was done prior to the accumulation of 

8,300 total flight cycles.

Prior to the accumulation of 15,000 total flight cycles, or within 3 months after the effective date of this AD, whichever occurs later. 

A300 B4–203 airplanes on which Airbus Service Bulletin 

A300–53–0297 was done on or after the accumulation 

of 8,300 total flight cycles.

Within 4,100 flight cycles after accomplishment of Airbus Service Bulletin A300–53– 

0297, or within 6 months after the effective date of this AD, whichever occurs later; 

except, for airplanes that, as of the effective date of this AD, have accumulated 

8,200 flight cycles or more since accomplishment of Airbus Service Bulletin A300– 

53–0297, within 3 months after the effective date of this AD. 

A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and 

B4–622R airplanes on which Airbus Service Bulletin 

A300–57–6053 was done prior to the accumulation of 

6,100 total flight cycles.

Prior to the accumulation of 11,500 total flight cycles, or within 3 months after the effective date of this AD, whichever occurs later. 

A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and 

B4–622R airplanes on which Airbus Service Bulletin 

A300–57–6053 was done on or after the accumulation 

of 6,100 total flight cycles.

Within 3,300 flight cycles after accomplishment of Airbus Service Bulletin A300–57– 

6053, or within 6 months after the effective date of this AD, whichever occurs later; 

except, for airplanes that, as of the effective date of this AD, have accumulated 

6,600 flight cycles or more since accomplishment of Airbus Service Bulletin A300– 

57–6053, within 3 months after the effective date of this AD. 

(2) Except as required by paragraph (f)(3) 

of this AD: If any crack is found during the 

inspection required by paragraph (f)(1) of this 

AD, before further flight, do a temporary or 

definitive repair, as applicable, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A300–53–0268, 

Revision 06, dated January 7, 2002 (for Model 

A300 B4–2C, B4–103, and B4–203 airplanes); 

or A300–57–6052, Revision 03, dated May 

27, 2002, including Airbus Drawings 

15R53810394, Issue A, dated December 21, 

1998, and 21R57110247, Issue A, dated June 

20, 1997 (for Model A300 B4–601, B4–603, 


jlentini on DSKJ8SOYB1PROD with RULES
11438 Federal Register / Vol. 75, No. 47 / Thursday, March 11, 2010 / Rules and Regulations 

B4–605R, B4–620, B4–622, and B4–622R 

airplanes). 

(3) If any crack found during the inspection 

required by paragraph (f)(1) of this AD cannot 

be repaired in accordance with Airbus 

Service Bulletin A300–53–0268, Revision 06, 

dated January 7, 2002; or A300–57–6052, 

Revision 03, dated May 27, 2002: Contact 

Airbus for repair instructions and before 

further flight repair the crack using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the European Aviation 

Safety Agency (EASA) (or its delegated 

agent.) 

Note 2: A repair is considered any 

modification that restores the original 

strength of the cracked part. 

(4) Submit an inspection report in 

accordance with Appendix 01 of Airbus 

Mandatory Service Bulletin A300–53A0387, 

dated September 12, 2008 (for Model A300 

B4–2C, B4–103, and B4–203 airplanes); or 

Airbus Mandatory Service Bulletin A300– 

57A6108, dated September 12, 2008 (for 

Model A300 B4–601, B4–603, B4–605R, B4– 

620, B4–622, and B4–622R airplanes); to the 

address identified on the reporting sheet, at 

the applicable time specified in paragraph 

(f)(4)(i) or (f)(4)(ii) of this AD. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

FAA AD Differences 

Note 3: This AD differs from the MCAI 

and/or service information as follows: 

Although the MCAI or Airbus Service 

Bulletin A300–53–0268, Revision 06, dated 

January 7, 2002; or A300–57–6052, Revision 

03, dated May 27, 2002; allows further flight 

after cracks are found during compliance 

with the required action, paragraph (f)(3) of 

this AD requires that the cracks be repaired 

before further flight. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to Attn: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 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. 

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: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), 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 EASA Airworthiness 

Directive 2009–0094, dated April 21, 2009 

(Correction: May 29, 2009), and the 

applicable service information specified in 

Table 2 of this AD, for related information. 

TABLE 2—RELATED SERVICE INFORMATION

Document Revision Date 

Airbus Mandatory Service Bulletin A300–53A0387, including Appendices 01 and 02 ........ Original .................................. September 12, 2008. 

Airbus Mandatory Service Bulletin A300–57A6108, including Appendices 01 and 02 ........ Original .................................. September 12, 2008. 

Airbus Service Bulletin A300–53–0268 ................................................................................. 06 .......................................... January 7, 2002. 

Airbus Service Bulletin A300–57–6052, including Airbus Drawings 15R53810394, Issue 

A, dated December 21, 1998, and 21R57110247, Issue A, dated June 20, 1997.

03 .......................................... May 27, 2002. 

Material Incorporated by Reference 

(i) You must use the service information 

contained in Table 3 of this AD to do the 

actions required by this AD, as applicable, 

unless the AD specifies otherwise. 

TABLE 3—MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Airbus Mandatory Service Bulletin A300–53A0387, including Appendices 01 and 02 ........ Original .................................. September 12, 2008. 

Airbus Mandatory Service Bulletin A300–57A6108, including Appendices 01 and 02 ........ Original .................................. September 12, 2008. 

Airbus Service Bulletin A300–53–0268 ................................................................................. 06 .......................................... January 7, 2002. 

Airbus Service Bulletin A300–57–6052, including Airbus Drawings 15R53810394, Issue 

A, dated December 21, 1998, and 21R57110247, Issue A, dated June 20, 1997.

03 .......................................... May 27, 2002. 

Airbus Service Bulletin A300–53–0268, 

Revision 06, dated January 7, 2002, has the 

following effective pages: 

Page No. Revision level shown on page Date shown on page 

1–6, 9, 10, 25–27 .............................................................. 06 January 7, 2002. 

7, 8, 11–24, 28–84 ............................................................ 05 June 9, 2000. 


jlentini on DSKJ8SOYB1PROD with RULES
Federal Register / Vol. 75, No. 47 / Thursday, March 11, 2010 / Rules and Regulations 11439 

Airbus Service Bulletin A300–57–6052, 

Revision 03, dated May 27, 2002, has the 

following effective pages: 

Page No. Revision level shown on page Date shown on page 

1–56 ...................................................................................................................... 03 .......................................................... May 27, 2002. 

DRAWING 15R53810394 

1–2 ........................................................................................................................ A ............................................................ December 21, 1998. 

DRAWING 21R57110247 

1–2 ........................................................................................................................ A ............................................................ May 28, 1997. 

3–4 ........................................................................................................................ A ............................................................ June 20, 1997. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 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.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 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 March 4, 

2010. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–5165 Filed 3–10–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0649; Directorate 

Identifier 2008–NM–218–AD; Amendment 

39–16225; AD 2010–06–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 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: 

Two incidents [of near mid-air collision] 

have occurred on Airbus A320 Family 

aircraft during [a] Resolution Advisory with 

Traffic Alert and Collision Avoidance System 

(TCAS). One of the Human-Machine Interface 

(HMI) factors was the lack of visibility of 

relevant information on the Primary Flight 

Display (PFD). 

This condition, if not corrected, could 

result in erroneous interpretation of TCAS 

Resolution Advisories, leading to an 

increased risk of mid-air collision. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective April 

15, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 15, 2010. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 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 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 July 15, 2009 (74 FR 34274). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Two incidents [of near mid-air collision] 

have occurred on Airbus A320 Family 

aircraft during [a] Resolution Advisory with 

Traffic Alert and Collision Avoidance System 

(TCAS). One of the Human-Machine Interface 

(HMI) factors was the lack of visibility of 

relevant information on the Primary Flight 

Display (PFD). 

This condition, if not corrected, could 

result in erroneous interpretation of TCAS 

Resolution Advisories, leading to an 

increased risk of mid-air collision. 

EIS1 [Electronic Instrument System] 

software standard V60 introduces 

modifications to the vertical speed indication 

to further improve the legibility in the case 

of TCAS Resolution Advisory. This 

modification consists of a change in the 

needle colour and thickness and an increase 

in width of the TCAS green band. 

For the reasons described above, this AD 

requires the introduction of the new software 

standard V60 and prohibits reinstallation of 

earlier software versions V32, V40 and V50. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Support for the NPRM 

Air Line Pilots Association (ALPA), 

International, supports the intent of the 

AD. 

Request To Shorten the Proposed 

Compliance Time 

ALPA states that the proposed 60- 

month compliance time is excessive, 

given that Airbus Mandatory Service 

Bulletin A320–31–1286 was issued in 

January, 2008. Based on the safety 

benefits of the AD as well as the 

minimal labor required to comply with 


jlentini on DSKJ8SOYB1PROD with RULES