8054 Federal Register / Vol. 78, No. 24 / Tuesday, February 5, 2013 / Proposed Rules 

except those on which Dassault Aviation 

modification M5741 has been embodied in 

production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electrical Power. 

(e) Reason 

This AD was prompted by reports of 

chafing between the tail strobe power supply 

and a hydraulic line. We are issuing this AD 

to prevent chafing between the tail strobe 

power supply and a hydraulic line, which 

could result in hydraulic fluid leakage and 

possible fire due to arcing, and consequent 

loss of control of the airplane due to 

structural failure of the tail. 

(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) Actions 

Within 65 days or 200 flight hours after the 

effective date of this AD, whichever occurs 

first: Modify the tail strobe power supply 

wire routing, in accordance with the 

Accomplishment Instructions of Dassault 

Mandatory Service Bulletin F900–431, dated 

November 8, 2011 (for Model MYSTERE– 

FALCON 900 airplanes); or Dassault 

Mandatory Service Bulletin F900EX–437, 

dated November 8, 2011 (for FALCON 900EX 

airplanes). 

(h) 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1137; 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 FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(i) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2012–0162, dated August 29, 2012, 

and the service information specified in 

paragraphs (j)(1)(i) and (j)(1)(ii) of this AD, 

for related information. 

(i) Dassault Mandatory Service Bulletin 

F900–431, dated November 8, 2011. 

(ii) Dassault Mandatory Service Bulletin 

F900EX–437, dated November 8, 2011. 

(2) For service information identified in 

this AD, contact Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, NJ 07606; 

telephone 201–440–6700; Internet http:// 

www.dassaultfalcon.com. You may review 

copies of the referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on January 

28, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–02450 Filed 2–4–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1321; Directorate 

Identifier 2011–NM–147–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain Airbus Model 

A310 series airplanes. The existing AD 

currently requires repetitive inspections 

for fatigue cracking of the area around 

the fasteners of the landing plate of the 

aileron access doors of the bottom skin 

panel of the wings, and related 

corrective action. The existing AD 

provides for an optional terminating 

action, which ends the repetitive 

inspections. Since we issued that AD, a 

reassessment of the previous fatigue 

threshold and inspection interval 

resulted in a determination that reduced 

inspection thresholds and intervals for 

accomplishment of the tasks are 

necessary. This proposed AD would 

reduce the initial inspection compliance 

time and intervals and provide 

additional terminating action options. 

We are proposing this AD to detect and 

correct fatigue cracking of the area 

around the fasteners of the landing plate 

of the aileron access doors and the 

bottom skin panel of the wings, which 

could result in reduced structural 

integrity of the wings. 

DATES: We must receive comments on 

this proposed AD by March 22, 2013. 

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, WA. 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, WA 

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 

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Federal Register / Vol. 78, No. 24 / Tuesday, February 5, 2013 / Proposed Rules 8055 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–1321; Directorate Identifier 

2011–NM–147–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 

On July 9, 2004, we issued AD 2004– 

15–07, Amendment 39–13741 (69 FR 

44592, July 27, 2004). That AD required 

actions intended to address an unsafe 

condition on Airbus Model A310 series 

airplanes. 

Since we issued AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, 

July 27, 2004), the manufacturer has 

done a reassessment of the previous 

fatigue threshold and inspection 

interval resulting in a recommendation 

of reduced inspection thresholds and 

intervals for accomplishment of the 

tasks. The European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community, has issued EASA 

Airworthiness Directive 2011–0125, 

dated June 30, 2011 (referred to after 

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

condition for the specified products. 

The MCAI states: 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France issued AD 2003–242(B) [which 

corresponds to FAA AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004)] to require an inspection programme 

for aeroplanes with pre- and post-Airbus 

modification 05106 configurations (Airbus 

SB A310–57–2004) in order to detect any 

crack located on the trailing edge of the wing 

bottom skin No.2 panel of the all-speedaileron servo control bay. A crack at this 

location, if not detected and corrected, would 

propagate towards the wing rear spar and 

ultimately into the wing fuel tank area. 

Undetected cracks would affect the structural 

integrity of the [left hand] LH and/or [right 

hand] RH wing. 

Since issuance of DGAC France AD 2003– 

242(B), a reassessment of the previous fatigue 

threshold and inspection interval has been 

completed. As a result of the reassessment, 

the inspection thresholds and intervals for 

accomplishment of the tasks as defined in 

Airbus SB A310–57–2082 have been adjusted 

and reduced. Airbus SB A310–57–2082 

Revision 03 has been published, in which the 

compliance time periods for these inspection 

thresholds and intervals have been amended. 

For the reasons stated above, this [EASA] 

AD retains the requirements of the DGAC 

France AD 2003–242(B), which is 

superseded, and requires implementation of 

the amended inspection programme. 

Corrective action includes doing a 

permanent repair (installing a repair 

plate and new landing plates), a 

temporary repair (crack-stop drilling 

and application of a protective coating) 

followed by repetitive inspections until 

a permanent repair is done, and a repair 

approved by the FAA or EASA (or its 

delegated agent). This proposed AD also 

adds optional permanent repairs. 

The initial inspection compliance 

times are dependent on the 

configuration (modification status, 

repair status, and crack length), and 

type of use (short range, long range, and 

normal). For airplanes without 

temporary repairs, the initial inspection 

compliance time ranges between 2,000 

total flight cycles or 10,200 total flight 

hours, whichever occurs first; and 

12,000 total flight cycles or 24,000 total 

flight hours, whichever occurs first. If 

the total flight cycles or total flight 

hours compliance time has been 

exceeded, the initial inspection 

compliance time (grace period) ranges 

between 200 flight cycles or 1,000 flight 

hours, to within 1,000 flight cycles or 

2,800 flight hours, whichever occurs 

first. 

For airplanes with temporary repairs, 

the initial inspection compliance time is 

dependant on crack length and ranges 

between 7 flight cycles or 35 flight 

hours, whichever occurs first, since the 

repair; to within 100 flight cycles or 200 

flight hours, whichever occurs first, 

since the repair. 

For airplanes with a temporary repair, 

the compliance time for completing the 

permanent repair ranges between 35 

flight cycles or 175 flight hours, 

whichever occurs first, after completing 

the temporary repair; to within 500 

flight cycles or 1,000 flight hours, 

whichever occurs first, after completing 

the temporary repair. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Airbus has issued the following 

service information. 

• Airbus Service Bulletin A310–57– 

2081, Revision 03, dated October 13, 

2010. 

• Airbus Mandatory Service Bulletin 

A310–57–2082, Revision 03, dated 

November 15, 2010. 

• Airbus Repair Instruction R573– 

49237, Repair To Crack In Trailing Edge 

Bottom Skin Panel No 2 Both Wings, 

Revision D, dated July 16, 2003. 

• Airbus Repair Instruction R573– 

49243, Repair to cracks in all speed 

aileron access door landing plates, both 

wings, Revision C, dated July 16, 2003. 

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 

Airbus Mandatory Service Bulletin 

A310–57–2082, Revision 03, dated 

November 15, 2010; and Airbus Service 

Bulletin A310–57–2081, Revision 03, 

dated October 13, 2010; specify to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions using 

a method approved by the FAA or the 

EASA (or its delegated agent). 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 58 products of U.S. registry. 

The actions that are required by AD 

2004–15–07, Amendment 39–13741 (69 

FR 44592, July 27, 2004), and retained 

in this proposed AD take about 2 workhours per product, at an average labor 

rate of $85 per work hour. Based on 

these figures, the estimated cost of the 

currently required actions is $170 per 

product. 

We estimate that it would take about 

4 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$19,720, or $340 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. We have 

no way of determining the number of 

products that may need these actions. 

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8056 Federal Register / Vol. 78, No. 24 / Tuesday, February 5, 2013 / Proposed Rules 

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); and 

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 

removing airworthiness directive (AD) 

2004–15–07, Amendment 39–13741 (69 

FR 44592, July 27, 2004), and adding the 

following new AD: 

Airbus: Docket No. FAA–2012–1321; 

Directorate Identifier 2011–NM–147–AD. 

(a) Comments Due Date 

We must receive comments by March 22, 

2013. 

(b) Affected ADs 

This AD supersedes AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004). 

(c) Applicability 

This AD applies to Airbus Model A310– 

203, –204, –221, –222, –304, –322, –324, and 

–325 airplanes, certificated in any category, 

all serial numbers; except for airplanes 

identified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) Airplanes that have been modified in 

service according to Airbus Service Bulletin 

A310–57–2081 or during production by 

Airbus modification 12525. 

(2) Airplanes that have been repaired 

according to Airbus Repair Inspection R573– 

49243 or R573–49237. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a reassessment 

of the previous fatigue threshold and 

inspection interval specified in AD 2004–15– 

07, Amendment 39–13741 (69 FR 44592, July 

27, 2004), which resulted in a determination 

that reduced inspection thresholds and 

intervals for accomplishment of the tasks are 

necessary. We are issuing this AD to detect 

and correct fatigue cracking of the area 

around the fasteners of the landing plate of 

the aileron access doors and the bottom skin 

panel of the wings, which could result in 

reduced structural integrity of the wings. 

(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) Retained Repetitive Inspections for 

Airplanes Without Airbus Modification 5106 

This paragraph restates the requirements of 

paragraph (a) of AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004). For airplanes on which Airbus 

Modification 5106 (Airbus Service Bulletin 

A310–57–2004, Revision 2, dated March 5, 

1990) has not been done as of August 31, 

2004 (the effective date of AD 2004–15–07): 

Within 2,000 flight cycles after the August 

31, 2004 (the effective date of AD 2004–15– 

07), or within 3,000 flight cycles after the last 

inspection done per paragraph (k) of AD 98– 

26–01, Amendment 39–10942 (63 FR 69179, 

December 16, 1998), whichever is first; do a 

high frequency eddy current (HFEC) 

inspection for cracking of the area around the 

fasteners of the landing plate of the wing 

bottom skin panel No. 2 of the left and right 

wings. Do the inspection per the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2082, dated June 

11, 2002. If no cracking is found, repeat the 

inspection thereafter at intervals not to 

exceed 1,900 flight cycles, until 

accomplishment of the terminating action 

specified in paragraph (j) of this AD. 

Accomplishment of the inspection required 

by paragraph (k) of this AD terminates the 

requirements of paragraph (g) of this AD. 

(h) Retained Repetitive Inspection for 

Airplanes With Airbus Modification 5106 

This paragraph restates the requirements of 

paragraph (b) of AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004). For airplanes on which Airbus 

Modification 5106 has been done as of 

August 31, 2004 (the effective date of AD 

2004–15–07): Do the HFEC inspection 

required by paragraph (g) of this AD at the 

applicable time specified in paragraph (h)(1), 

(h)(2), (h)(3), or (h)(4) of this AD. If no 

cracking is found, repeat the inspection 

thereafter at intervals not to exceed 1,900 

flight cycles, until accomplishment of the 

terminating action specified in paragraph (j) 

of this AD. Accomplishment of the 

inspection required by paragraph (k) of this 

AD terminates the requirements of paragraph 

(h) of this AD. 

(1) For airplanes that have accumulated 

fewer than 17,000 total flight cycles since the 

date of issuance of the original Airworthiness 

Certificate or the date of issuance of the 

original Export Certificate of Airworthiness, 

whichever is first, as of August 31, 2004 (the 

effective date of AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004)): Inspect prior to the accumulation of 

18,000 total flight cycles. 

(2) For airplanes that have accumulated 

17,000 or more total flight cycles, but fewer 

than 19,001 total flight cycles since the date 

of issuance of the original Airworthiness 

Certificate or the date of issuance of the 

original Export Certificate of Airworthiness, 

whichever is first, as of August 31, 2004 (the 

effective date of AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004)): Inspect within 2,000 flight cycles 

after August 31, 2004 (the effective date of 

AD 2004–15–07). 

(3) For airplanes that have accumulated 

19,001 or more total flight cycles, but fewer 

than 21,001 total flight cycles since the date 

of issuance of the original Airworthiness 

Certificate or the date of issuance of the 

original Export Certificate of Airworthiness, 

whichever is first, as of August 31, 2004 (the 

effective date of AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004)): Inspect with 1,200 flight cycles after 

August 31, 2004 (the effective date of AD 

2004–15–07). 

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(4) For airplanes that have accumulated 

21,001 or more total flight cycles since the 

date of issuance of the original Airworthiness 

Certificate or the date of issuance of the 

original Export Certificate of Airworthiness, 

whichever is first, as of August 31, 2004 (the 

effective date of AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004)): Inspect within 500 flight cycles after 

August 31, 2004 (the effective date of AD 

2004–15–07). 

(i) Retained Corrective Action 

This paragraph restates the requirements of 

paragraph (c) of AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004). If any cracking is found during any 

inspection required by paragraph (g) or (h) of 

this AD: Before further flight, do the actions 

required by either paragraph (i)(1) or (i)(2) of 

this AD. 

(1) Do a permanent repair of the area by 

doing the applicable corrective actions per 

the Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2082, dated June 

11, 2002. Accomplishment of the permanent 

repair terminates the repetitive inspections 

required by this AD for the repaired area 

only. 

(2) Do the terminating action specified in 

paragraph (j) of this AD. 

(j) Retained Optional Terminating Action, 

With New Service Information and Options 

This paragraph restates the retained 

optional terminating action information 

specified in paragraph (d) of AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004), with new service information and new 

options. Modification of the landing plate of 

the aileron access doors of the wing bottom 

skin panel No. 2 of the left and right wings 

by doing all the actions, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2081, dated June 

11, 2002, or Airbus Service Bulletin A310– 

57–2081, Revision 03, dated October 13, 

2010; or by doing the repair in accordance 

with Airbus Repair Instruction R573–49243, 

Revision C, dated July 16, 2003, or Airbus 

Repair Instruction R573–49237, Revision D, 

dated July 16, 2003; terminates the 

requirements of this AD. Where Airbus 

Service Bulletin A310–57–2081, dated June 

11, 2002; and Airbus Service Bulletin A310– 

57–2081, Revision 03, dated October 13, 

2010; specify contacting the manufacturer for 

disposition of certain repair conditions that 

might be associated with the modification 

procedure, this AD requires that the repair be 

done in accordance with a method approved 

by either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; the Direction Ge ́ne ́rale de l’Aviation 

Civile (DGAC) (or its delegated agent); or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

(k) New Inspections, Related Investigative 

Actions, and Corrective Actions 

Except as specified in paragraph (m)(1) of 

this AD, at the applicable time specified in 

Paragraph 1.E., ‘‘Compliance,’’ of Airbus 

Mandatory Service Bulletin A310–57–2082, 

Revision 03, dated November 15, 2010: Do a 

high frequency eddy current (HFEC) 

inspection to detect cracking of the area 

around the fasteners of the landing plate of 

the wing bottom skin panel No. 2 of the left 

and right wings; and do all applicable 

corrective actions; in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–57–2082, 

Revision 03, dated November 15, 2010, 

except as required by paragraph (m)(2) of this 

AD. Do all applicable corrective actions 

before further flight. Repeat the inspection of 

the area around the fasteners of the landing 

plate of the wing bottom skin panel number 

2 of the left and right wings thereafter at the 

applicable intervals, including the 

compliance times for post temporary repair 

inspections, specified in Paragraph 1.E., 

‘‘Compliance,’’ of Airbus Mandatory Service 

Bulletin A310–57–2082, Revision 03, dated 

November 15, 2010, except as specified in 

paragraph (m)(3) of this AD. The temporary 

repair of cracks, as identified in Airbus 

Mandatory Service Bulletin A310–57–2082, 

Revision 03, dated November 15, 2010, does 

not constitute terminating action for the 

repetitive inspections required by this AD. 

Accomplishment of the inspection required 

by this paragraph terminates the 

requirements of paragraphs (g) and (h) of this 

AD. Doing the modification specified in 

paragraph (j) of this AD terminates the 

repetitive inspections required by this 

paragraph. 

(l) New Permanent Repair 

For airplanes on which the temporary 

repair as specified in Airbus Mandatory 

Service Bulletin A310–57–2082 has been 

done, within the applicable time specified in 

Paragraph 1.E., ‘‘Compliance,’’ of Airbus 

Mandatory Service Bulletin A310–57–2082, 

Revision 03, dated November 15, 2010: Do 

the permanent repair, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–57–2082, 

Revision 03, dated November 15, 2010, 

except as provided by paragraph (m)(2) of 

this AD. 

(m) New Exceptions to Service Information 

(1) Where Paragraph 1.E., ‘‘Compliance,’’ of 

Airbus Mandatory Service Bulletin A310–57– 

2082, Revision 03, dated November 15, 2010, 

specifies a compliance time ‘‘from receipt of 

this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(2) Where Airbus Mandatory Service 

Bulletin A310–57–2082, Revision 03, dated 

November 15, 2010, specifies to contact 

Airbus for repair: Before further flight, repair 

the crack using a method approved by either 

the Manager, International Branch, ANM– 

116; or EASA (or its delegated agent). 

(3) Where Paragraph 1.E., ‘‘Compliance,’’ of 

Airbus Mandatory Service Bulletin A310–57– 

2082, Revision 03, dated November 15, 2010, 

specifies to contact Airbus for inspection 

intervals, this AD requires using an 

inspection interval approved by either the 

Manager, International Branch, ANM–116; or 

EASA (or its delegated agent). 

(n) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraphs (k) and (l) of 

this AD, if those actions were performed 

before the effective date of this AD using the 

service information specified in paragraph 

(n)(1)(i), (n)(1)(ii), or (n)(1)(iii) of this AD, 

which is not incorporated by reference in this 

AD. 

(i) Airbus Service Bulletin A310–57–2082, 

dated June 11, 2002. 

(ii) Airbus Service Bulletin A310–57–2082, 

Revision 01, dated August 22, 2003. 

(iii) Airbus Service Bulletin A310–57– 

2082, dated June 11, 2002. 

(2) This paragraph provides credit for the 

modification of the landing plate of the 

aileron access doors of the wing bottom skin 

panel No. 2 of the left and right wings 

required by paragraph (j) of this AD, if those 

actions were performed before the effective 

date of this AD using the service information 

specified in paragraph (n)(2)(i) or (n)(2)(ii) of 

this AD, which is not incorporated by 

reference in this AD, except where this 

service information specifies contacting the 

manufacturer for disposition of certain repair 

conditions that might be associated with the 

modification procedure, this AD requires that 

the repair be done in accordance with a 

method approved by either the Manager, 

International Branch, ANM–116; or the 

EASA (or its delegated agent). 

(i) Airbus Service Bulletin A310–57–2081, 

Revision 01, dated February 26, 2003. 

(ii) Airbus Service Bulletin A310–57–2081, 

Revision 02, dated October 18, 2007. 

(o) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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, WA 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 FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(3) AMOCs approved previously in 

accordance with AD 2004–15–07, 

Amendment 39–13741 (69 FR 44592, July 27, 

2004), are approved as AMOCs for the 

corresponding provisions of this AD. 

(p) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2011–0125, dated June 30, 2011, 

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8058 Federal Register / Vol. 78, No. 24 / Tuesday, February 5, 2013 / Proposed Rules 

and the service information specified in 

paragraphs (p)(1)(i) through (p)(1)(vi) of this 

AD, for related information. 

(i) Airbus Mandatory Service Bulletin 

A310–57–2082, Revision 03, dated November 

15, 2010. 

(ii) Airbus Service Bulletin A310–57–2081, 

dated June 11, 2002. 

(iii) Airbus Service Bulletin A310–57– 

2081, Revision 03, dated October 13, 2010. 

(iv) Airbus Service Bulletin A310–57– 

2082, dated June 11, 2002. 

(v) Airbus Repair Instruction R573–49237, 

Revision D, dated July 16, 2003. 

(vi) Airbus Repair Instruction R573–49243, 

Revision C, dated July 16, 2003. 

(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; 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, WA. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on January 

20, 2013. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–02448 Filed 2–4–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0270; Directorate 

Identifier 2011–NM–113–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for all Fokker Services B.V. Model F.27 

Mark 050 airplanes, and Model F.28 

Mark 0070 and 0100 airplanes. That 

NPRM proposed to require inspecting 

and, if necessary, adjusting, the torque 

values of nuts on circuit breakers, 

contactors, and terminal blocks of the 

electrical power center (EPC) and 

battery relay panel. This proposed AD 

would also require inspecting to 

determine if certain parts are installed, 

and installing the parts if necessary. 

This action revises that NPRM by 

adding a previously omitted terminal 

block to the required actions. We are 

proposing this AD to detect and correct 

loose nuts, which could result in arcing 

and potentially an onboard fire, possibly 

resulting in damage to the airplane and 

injury to occupants or maintenance 

personnel. Since these actions impose 

an additional burden over that proposed 

in the NPRM, we are reopening the 

comment period to allow the public the 

chance to comment on these proposed 

changes. 

DATES: We must receive comments on 

this proposed AD by March 22, 2013. 

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 Fokker 

Services B.V., Technical Services Dept., 

P.O. Box 231, 2150 AE Nieuw-Vennep, 

the Netherlands; telephone +31 (0)252– 

627–350; fax +31 (0)252–627–211; email 

technicalservices.fokkerservices

@stork.com; Internet http:// 

www.myfokkerfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. 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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; 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–2012–0270; Directorate Identifier 

2011–NM–113–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 

We proposed to amend 14 CFR part 

39 with an earlier NPRM for the 

specified products, which was 

published in the Federal Register on 

March 21, 2012 (77 FR 16486). That 

earlier NPRM proposed to require 

actions intended to address the unsafe 

condition for the products listed above. 

Since that NPRM (77 FR 16486, 

March 21, 2012) was issued, we have 

determined that an additional terminal 

block used in some Model F.28 Mark 

0100 airplanes needs to be included in 

the required actions proposed in the 

earlier NPRM. European Aviation Safety 

Agency (EASA) has issued 

Airworthiness Directive 2012–0050, 

dated March 27, 2012 (referred to after 

this as ‘‘the MCAI’’), to add that 

terminal block to their required actions. 

The MCAI states: 

In December 1989, Fokker issued Service 

Bulletin (SB) SBF50–24–A013 and SBF100– 

24–A011 (both Alert Bulletins) to instruct 

operators to inspect and adjust several torque 

values of bus bars and contactors in the EPC. 

The Civil Aviation Authority of The 

Netherlands (CAA–NL, formerly RLD) issued 

AD (BLA) 89–159 and BLA 89–157 

respectively (both now at issue 2), to require 

operators of the affected aeroplanes to 

comply with the instructions of these SB’s. 

Since those [Dutch] ADs were issued, 

several operators reported finding loose nuts 

on contactors in the EPC of Fokker 50/60 

aeroplanes in post-SBF50–24–A013 

configuration and on Fokker 70/100 

aeroplanes in post-SBF100–24–A011 

configuration. In some cases, the findings 

included damaged (burned) contactors. 

This condition, if not detected and 

corrected, could lead to arcing and, in 

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