Federal Register / Vol. 77, No. 39 / Tuesday, February 28, 2012 / Proposed Rules 11793 

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: 

Saab AB, Saab Aerosystems: Docket No. 

FAA–2012–0184; Directorate Identifier 

2011–NM–118–AD. 

(a) Comments Due Date 

We must receive comments by April 13, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Saab AB, Saab 

Aerosystems Model SAAB 2000 airplanes; 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 92. 

(e) Reason 

This AD was prompted by reports that 

environmentally friendly de-icing agents 

used on certain electrical connectors and 

braids could cause corrosion damage. We are 

issuing this AD to detect and correct 

corrosion of critical system wiring, which 

could result in arcing and, in combination 

with other factors, a fire and consequent 

damage to the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspection 

Within 24 months after the effective date 

of this AD, do a detailed inspection for 

corrosion of the electrical and electronics 

installation, at the locations specified in and 

in accordance with the Accomplishment 

Instructions of SAAB Service Bulletin 2000– 

92–005, Revision 01, dated March 1, 2011; 

and SAAB Service Bulletin 2000–92–006, 

Revision 01, dated August 18, 2010. These 

inspections do not need to be accomplished 

concurrently. 

(h) Corrective Action 

If any corrosion is found during any 

inspection required in paragraph (g) of this 

AD: Before next flight, repair each affected 

harness braid or replace each affected 

component and/or wiring harness, as 

applicable, in accordance with the 

Accomplishment Instructions of SAAB 

Service Bulletin 2000–92–005, Revision 01, 

dated March 1, 2011; and SAAB Service 

Bulletin 2000–92–006, Revision 01, dated 

August 18, 2010. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

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

this AD, if those actions were performed 

before the effective date of this AD using 

according to SAAB Service Bulletin 2000– 

92–005, dated May 5, 2010; and SAAB 

Service Bulletin 2000–92–006, dated 

March 29, 2010. 

(j) Reporting Requirement 

Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (g) of this AD, using 

the Feedback Form in SAAB Service Bulletin 

2000–92–005, Revision 01, dated March 1, 

2011; and SAAB Service Bulletin 2000–92– 

006, Revision 01, dated August 18, 2010. 

Send the report to SAAB Aerotech, Support 

Services Division, SE–581 88 Linkoping, 

Sweden; fax +46 13 18 4874; email 

saab2000.techsupport@saabgroup.com; at the 

applicable time specified in paragraph (i)(1) 

or (i)(2) of this AD. The report must include 

the level of corrosion found on each 

connector. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) 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. 

(k) Other FAA AD Provisions 

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. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Shahram Daneshmandi, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1112; fax (425) 

227–1149. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding 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. 

(l) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0079, dated May 5, 2011, and 

the service information specified in 

paragraphs (l)(1) and (l)(2) of this AD, for 

related information. 

(1) SAAB Service Bulletin 2000–92–005, 

Revision 01, dated March 1, 2011. 

(2) SAAB Service Bulletin 2000–92–006, 

Revision 01, dated August 18, 2010. 

Issued in Renton, Washington, on February 

14, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–4646 Filed 2–27–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0185; Directorate 

Identifier 2011–NM–001–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A300 B4–103, B4–203, 

and B4–2C airplanes, and Model B4– 

600, B4–600R, and F4–600R series 

airplanes, and Model C4–605R Variant F 

airplanes (collectively called A300–600 

series airplanes). This proposed AD was 

prompted by reports of cracking in the 

forward lug of the main landing gear 

(MLG) rib 5 aft bearing attachment. This 

proposed AD would require repetitive 

inspections for cracking of the left-hand 

(LH) and right-hand (RH) wing MLG rib 

5 aft bearing forward lugs and repair if 

necessary. We are proposing this AD to 

detect and correct cracking of the LH 

and RH wing MLG rib 5 aft bearing 

forward lugs which, if not corrected, 

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11794 Federal Register / Vol. 77, No. 39 / Tuesday, February 28, 2012 / Proposed Rules 

could affect the structural integrity of 

the MLG attachment, which could result 

in MLG collapse during landing or 

rollout with consequent damage to the 

airplane and injury to occupants. 

DATES: We must receive comments on 

this proposed AD by April 13, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this proposed 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; email: 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may review copies of the referenced 

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. 

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 this proposed AD, 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. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–0185; Directorate Identifier 

2011–NM–001–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0250, 

dated November 29, 2010 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During routine visual inspection, a crack 

has been found in the wing MLG [main 

landing gear] rib 5 aft bearing forward lug on 

two A310 in-service aeroplanes. Laboratory 

examination of cracked ribs confirmed that 

the crack was due to the presence of pitting 

corrosion in the forward lug hole. Also on 

both aeroplanes medium to heavy corrosion 

was found in the forward lugs on the 

opposite wing after removal of the bushes. 

Similarly to A310 aeroplanes, A300 and 

A300–600 aeroplanes are concerned by this 

situation which, if not detected, could affect 

the structural integrity of the MLG 

attachment. 

The aim of the [EASA] Emergency 

Airworthiness Directive (EAD) 2006–0372–E 

[which corresponds to FAA AD 2007–03–18, 

Amendment 39–14929 (72 FR 5919, February 

8, 2007)] was to mandate, for A300 and 

A300–600 aeroplanes, repetitive detailed 

visual inspections (DVI) of wing MLG rib 5 

aft bearing forward lugs for detection of 

through cracks. 

Since then, in order to ensure the detection 

of any crack in the forward lug of the RH 

[right-hand] and LH [left-hand] MLG rib 5 aft 

bearing attachment at an early stage, Airbus 

has developed a new inspection by means of 

ultrasonic method. Due to the early crack 

detection possibility, this new means of 

inspection also enables extension of the 

inspection interval. 

For technical reasons, this new means of 

inspection is only applicable to A300B4, C4, 

and F4 and A300–600 aeroplane series (not 

to A300B2 aeroplane series). 

For these reasons, this new [EASA] AD 

* * * adds new inspection program 

requirements [a revised detailed inspection, 

optional ultrasonic inspections, and repair if 

necessary]. 

As an option, a modification which 

includes installing bushings with an 

increased interference fit in the aft 

bearing forward lugs terminates the 

repetitive inspections. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued the following 

service bulletins: 

• Mandatory Service Bulletin A300– 

57–0249, Revision 02, dated June 18, 

2010 (for Model A300–B4–103, B4–2C, 

and B4–203 airplanes). 

• Mandatory Service Bulletin A300– 

57–0251, including Appendix 01, dated 

August 8, 2007 (for Model A300 B4– 

103, B4–203 and B4–2C airplanes). 

• Service Bulletin A300–57–6106, 

Revision 02, dated June 18, 2010 (for 

Model A300 B4–601, B4–603, B4–605R, 

B4–620, B4–622, B4–622R, F4–605R, 

F4–622R, and C4–605R airplanes). 

• Mandatory Service Bulletin A300– 

57–6107, including Appendix 01, dated 

August 8, 2007 (for Model A300 B4– 

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

B4–622R, C4–605R, F4–605R, and F4– 

622R airplanes). 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

Although the MCAI allows further 

flight after cracks are found during 

compliance with the required action, 

paragraph (i) of this AD requires that 

you repair the cracks before further 

flight. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 165 products of U.S. 

registry. We also estimate that it would 

take about 3 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

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Federal Register / Vol. 77, No. 39 / Tuesday, February 28, 2012 / Proposed Rules 11795 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$42,075, or $255 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 52 work-hours and require parts 

costing $4,590, for a cost of $9,010 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed regulation: 

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); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. 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 proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Airbus: Docket No. FAA–2012–0185; 

Directorate Identifier 2011–NM–001–AD. 

(a) Comments Due Date 

We must receive comments by April 13, 

2012. 

(b) Affected ADs 

This AD affects AD 2007–03–18, 

Amendment 39–14929 (72 FR 5919, February 

8, 2007). 

(c) Applicability 

This AD applies to Airbus Model A300 B4– 

2C, B4–103, B4–203 airplanes; Model B4– 

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

622R, F4–605R and F4–622R airplanes; and 

Model A300 C4–605R Variant F airplanes; 

certificated in any category; all serial 

numbers except for airplanes identified in 

paragraphs (c)(1), (c)(2), and (c)(3) of this AD. 

(1) Airplanes on which LH (left-hand) and 

RH (right-hand) wing main landing gear 

(MLG) rib 5 forward lugs have oversized 

interference fit bushings installed per 

drawing R57240221. 

(2) Model A300 B4–103, B4–203, and B4– 

2C airplanes on which Airbus Mandatory 

Service Bulletin A300–57–0249 has been 

done in service on the LH and RH wing. 

(3) Model A300–600 series airplanes on 

which Airbus Service Bulletin A300–57– 

6106 has been done in service on the LH and 

RH wing. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57: Wings. 

(e) Reason 

This AD was prompted by reports of 

cracking in the forward lug of the MLG rib 

5 aft bearing attachment. We are issuing this 

AD to detect and correct cracking of the LH 

and RH wing MLG rib 5 aft bearing forward 

lugs which, if not corrected, could affect the 

structural integrity of the MLG attachment, 

which could result in MLG collapse during 

landing or rollout with consequent damage to 

the airplane and injury to occupants. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspections 

Except as provided by paragraph (h) of this 

AD, before the accumulation of 12,000 total 

flight cycles since new, or within 12,000 

flight cycles since the most recent MLG rib 

5 replacement, if applicable, or within 10 

days after the effective date of this AD, 

whichever occurs latest, do a detailed 

inspection or an ultrasonic inspection for 

cracking of the LH and RH MLG rib 5 aft 

bearing forward lugs, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57–0251, 

including Appendix 01, dated August 8, 2007 

(for Model A300 B4–103, B4–203, and B4–2C 

airplanes); or Airbus Mandatory Service 

Bulletin A300–57–6107, including Appendix 

01, dated August 8, 2007 (for Model A300– 

600 series airplanes). Repeat the applicable 

inspections thereafter at the applicable 

interval specified in paragraph (g)(1) or (g)(2) 

of this AD, until the modification specified 

in paragraph (j) of this AD is accomplished. 

(1) Repeat the detailed inspections at 

intervals not to exceed 100 flight cycles. 

(2) Repeat the ultrasonic inspections at 

intervals not to exceed 675 flight cycles. 

(h) Exception 

For airplanes on which an inspection 

required by AD 2007–03–18, Amendment 

39–14929 (72 FR 5919, February 8, 2007), has 

been done as of the effective date of this AD: 

Within 100 flight cycles after doing the most 

recent inspection required by AD 2007–03– 

18, or within 10 days after the effective date 

of this AD, whichever occurs later, do a 

detailed or ultrasonic inspection as specified 

in paragraph (g) of this AD. Repeat the 

applicable inspection thereafter at the times 

specified in paragraph (g) of this AD. 

(i) Repair 

If any cracking is detected during any 

detailed or ultrasonic inspection of the LH 

and RH MLG rib 5 aft bearing forward lugs 

required by paragraph (g) of this AD, before 

further flight, repair using a method 

approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent). 

(j) Optional Terminating Modification 

Performing the applicable actions specified 

in paragraphs (j)(1), (j)(2), (j)(3) and (j)(4) of 

this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57–0249, 

Revision 02, dated June 18, 2010 (for Model 

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

or Airbus Service Bulletin A300–57–6106, 

Revision 02, dated June 18, 2010 (for Model 

A300–600 series airplanes); terminates the 

repetitive inspections required by this AD. 

(1) Perform a general visual inspection and 

dye penetrant flaw detection inspection for 

corrosion and damage of the bore and 

spotfaces of the lug. 

(2) Determine that the diameter of the bore 

of the lug (dimension Y) is within the 

tolerance specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

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11796 Federal Register / Vol. 77, No. 39 / Tuesday, February 28, 2012 / Proposed Rules 

Bulletin A300–57–0249, Revision 02, dated 

June 18, 2010 (for Model A300 B4–103, B4– 

203, and B4–2C airplanes); or Airbus Service 

Bulletin A300–57–6106, Revision 02, dated 

June 18, 2010 (for Model A300–600 series 

airplanes). 

(3) If damage or corrosion is detected 

during any inspection specified in paragraph 

(j)(1) of this AD, or if dimension Y is outside 

the tolerance specified in the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57–0249, 

Revision 02, dated June 18, 2010 (for Model 

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

or Airbus Service Bulletin A300–57–6106, 

Revision 02, dated June 18, 2010 (for Model 

A300–600 series airplanes); repair using a 

method approved by either the Manager, 

International Branch, ANM 116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent). 

(4) Install bushings with an increased 

interference fit in the aft bearing forward 

lugs, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57–0249, 

Revision 02, dated June 18, 2010 (for Model 

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

or Airbus Service Bulletin A300–57–6106, 

Revision 02, dated June 18, 2010 (for Model 

A300–600 series airplanes). 

(k) Terminating Action for AD 2007–03–18, 

Amendment 39–14929 (72 FR 5919, 

February 8, 2007) 

Doing the inspection required by paragraph 

(g) of this AD terminates the requirements of 

AD 2007–03–18, Amendment 39–14929 (72 

FR 5919, February 8, 2007), for that airplane. 

(l) Reporting 

Submit a report (including both positive 

and negative findings), using the applicable 

report sheet attached to Airbus Mandatory 

Service Bulletin A300–57–0251, including 

Appendix 01, dated August 8, 2007 (for 

Model A300 B4–103, B4–203, and B4–2C 

airplanes); or Airbus Mandatory Service 

Bulletin A300–57–6107, including Appendix 

01, August 8, 2007 (for Model A300–600 

series airplanes); of the first inspection 

required by paragraph (g) of this AD. Submit 

the report to Airbus, Customer Services 

Directorate, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex France, Attn: SEDCC1 

Technical Data and Documentation Services; 

fax: (+33) 5 61 93 28 06; email: sb.reporting@

airbus.com; at the applicable time specified 

in paragraph (l)(1) or (l)(2) of this AD. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) 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. 

(m) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using the applicable 

service bulletins specified in paragraphs 

(m)(1), (m)(2), (m)(3), and (m)(4) of this AD. 

(1) Airbus Service Bulletin A300–57–0249, 

dated May 22, 2007 (for Model A300 B4–2C, 

B4–103, and B4–203 airplanes). 

(2) Airbus Service Bulletin A300–57–0249, 

Revision 01, dated December 19, 2007 (for 

Model A300 B4–2C, B4–103, and B4–203 

airplanes). 

(3) Airbus Service Bulletin A300–57–6106, 

dated May 22, 2007 (Model A300 B4–601, 

B4–603, B4–605R, B4–620, B4–622, B4– 

622R, F4–605R, F4–622R, and Model A300 

C4–605R Variant F airplanes). 

(4) Airbus Service Bulletin A300–57–6106, 

Revision 01, dated January 28, 2008 (Model 

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

B4–622, B4–622R, F4–605R, F4–622R, and 

Model A300 C4–605R Variant F airplanes). 

(n) Other FAA AD Provisions 

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. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it 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. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding 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. 

(o) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2010–0250, dated November 29, 

2010, and the service information in 

paragraphs (o)(1), (o)(2), (o)(3), and (o)(4) of 

this AD, for related information. 

(1) Airbus Mandatory Service Bulletin 

A300–57–0249, Revision 02, dated June 18, 

2010. 

(2) Airbus Mandatory Service Bulletin 

A300–57–0251, including Appendix 01, 

dated August 8, 2007. 

(3) Airbus Service Bulletin A300–57–6106, 

Revision 02, dated June 18, 2010. 

(4) Airbus Mandatory Service Bulletin 

A300–57–6107, including Appendix 01, 

August 8, 2007. 

Issued in Renton, Washington, on February 

13, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–4644 Filed 2–27–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

Docket No. FAA–2012–0131; Airspace 

Docket No. 12–ANM–2 

Proposed Amendment of Class E 

Airspace; Rock Springs, WY 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

amend Class E airspace at Rock SpringsSweetwater County Airport, Rock 

Springs, WY. Decommissioning of the 

Rock Springs Tactical Air Navigation 

System (TACAN) has made this action 

necessary for the safety and 

management of Instrument Flight Rules 

(IFR) operations at the airport. This 

action also would adjust the geographic 

coordinates of the airport. 

DATES: Comments must be received on 

or before April 13, 2012. 

ADDRESSES: Send comments on this 

proposal to the U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590; telephone (202) 

366–9826. You must identify FAA 

Docket No. FAA–2012–0131; Airspace 

Docket No. 12–ANM–2, at the beginning 

of your comments. You may also submit 

comments through the Internet at 

http://www.regulations.gov. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS