Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Proposed Rules 51117 

Eurocopter or UTC Actuation Systems/ 

Goodrich Actuation Systems. 

Accordingly, we have included all costs 

in our cost estimate. 

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 proposed 

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, 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 to the extent that it justifies 

making a regulatory distinction; 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 an economic 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 airworthiness 

directive (AD): 

Eurocopter France (Eurocopter) Helicopters: 

Docket No. FAA–2013–0737; Directorate 

Identifier 2012–SW–111–AD. 

(a) Applicability 

This AD applies to the following model 

helicopters, certificated in any category, with 

a part-numbered main servo-control listed 

below: overhauled or repaired by UTC 

Actuation Systems/Goodrich Actuation 

Systems between June 1, 2008, and 

September 15, 2012, inclusive; or with a 

serial number listed in Appendix 1 of 

Eurocopter Emergency Alert Service Bulletin 

Nos. 67.00.45 or 67.19, both Revision 1, and 

both dated December 5, 2012 (EASB): 

(1) Model AS332C, AS332L, AS332L1, and 

AS332L2 helicopters with main servocontrol, part number (P/N) SC7202, SC7202– 

(all dash numbers), SC7203, SC7203–(all 

dash numbers), SC7221, or SC7221–(all dash 

numbers), installed; and 

(2) Model SA330J helicopters with main 

servo-control P/N SC7111, SC7111–(all dash 

numbers) SC7112, or SC7112–(all dash 

numbers), installed. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

missing crimping on a ball joint of a main 

servo-control end-fitting. This condition 

could result in failure of a main servo-control 

upper end fitting, failure of the flight 

controls, and loss of control of the helicopter. 

(c) Comments Due Date 

We must receive comments by October 21, 

2013. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Within 85 hours time-in-service (TIS): 

(i) Using a light source, inspect the ball 

joint of the upper end-fitting of the main 

servo control for crimping in accordance 

with Detail A and Detail B, Figure 1, of the 

EASB applicable to your model helicopter. 

(A) If the upper ball joint is not crimped 

and the ball joint slips a distance of 1 

millimeter (mm) or greater, replace the servocontrol with an airworthy servo-control. 

(B) If the upper ball joint is not crimped 

and the ball joint slips a distance of less than 

1mm, either crimp the ball joint or replace 

the servo-control with an airworthy servocontrol. 

(ii) Using a light source, inspect the ball 

joint of the lower end-fitting of the main 

servo-control for crimping in accordance 

with Detail A and Detail B, Figure 1, of the 

EASB applicable to your model helicopter. If 

the lower ball joint is not crimped, crimp the 

ball joint. 

(2) Prior to installing any servo-control that 

is affected by this AD, perform the required 

actions in accordance with paragraphs (e)(1) 

of this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Wilbanks, 

Aviation Safety Engineer, Rotorcraft 

Certification Office, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5110; 

email matt.wilbanks@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2012–0248, dated November 20, 2012. 

You may view the EASA AD on the Internet 

at http://www.regulations.gov in Docket No. 

FAA–2013–0737. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6730, Rotor Flight Control—Rotorcraft 

Servo System. 

Issued in Fort Worth, Texas, on August 12, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–20312 Filed 8–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0698; Directorate 

Identifier 2012–NM–136–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 

airworthiness directive (AD) 2006–06– 

14, that applies to certain Airbus Model 


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A318–100 and A319–100 series 

airplanes, A320–111 airplanes, A320– 

200 series airplanes, and A321–100 and 

A321–200 series airplanes. AD 2006– 

06–14 requires operators to review the 

airplane’s maintenance records to 

determine the part numbers of the 

magnetic fuel level indicators (MFLIs) of 

the wing fuel tanks, and related 

investigative and corrective actions if 

necessary. Since we issued AD 2006– 

06–14, we received information that the 

related investigative actions of the 

existing AD are not fully effective and 

that an affected MFLI could still be 

installed on airplanes on which the 

related investigative actions were 

accomplished. This proposed AD would 

also require an inspection (improved 

method) to determine the part numbers 

of the MFLIs, and, if necessary, 

replacement of the MFLI or repair. We 

are proposing this AD to prevent an 

ignition source in the wing fuel tank in 

the event of a lightning strike, which 

could result in a fire or explosion. 

DATES: We must receive comments on 

this proposed AD by October 4, 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, 

Airworthiness Office—EAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1405; 

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–2013–0698; Directorate Identifier 

2012–NM–136–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 March 10, 2006, we issued AD 

2006–06–14, Amendment 39–14523 (71 

FR 15023, March 27, 2006), (‘‘AD 2006– 

06–14’’). That AD required actions 

intended to address an unsafe condition 

on Airbus Model A318–111 and –112 

airplanes; Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 

airplanes; A320–111 airplanes; Model 

A320–211, –212, –214, –231, –232, and 

–233 airplanes; Model A321–111, –112, 

and –131 airplanes; and Model A321– 

211, –212, –213, –231, and –232 

airplanes. 

Since we issued AD 2006–06–14, the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0119, 

dated July 4, 2012 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

In 2005, several in-service occurrences 

were reported of finding wear and/or 

detachment of the top stop of magnetic fuel 

level indicators (MFLI), either observed 

during tank maintenance activities, or on 

MFLI returned to the MFLI manufacturer. 

The investigation results indicated that the 

wear of the top stop retaining ‘S’ shaped wire 

had been caused by repetitive impact with 

the float, resulting in complete detachment of 

the top stop. 

This condition, if not detected and 

corrected, could lead an MFLI top stop to 

come into contact with a probe, which could, 

in the event of a lightning strike, create an 

ignition source in the fuel tank vapour space, 

possibly resulting in a fuel tank explosion 

and consequent loss of the aeroplane. 

DGAC France issued AD F–2005–108 

(EASA approval 2005–6026) [http://

ad.easa.europa.eu/ad/F–2005–108] 

[corresponding FAA AD 2006–06–14] to 

require identification (by inspection) and 

replacement of the affected metallic MFLI 

(3508802-xx series with the ‘S’ shaped 

retaining wire) with a metallic MFLI with the 

top stop retained by a ‘trapped wire’, or with 

a composite MFLI. 

Since that [French] AD was issued, it has 

been identified that the inspection procedure 

(visual check) detailed in Airbus Service 

Bulletin (SB) A320–28–1138 was not fully 

effective, and that affected MFLI could still 

be fitted on aeroplanes which have passed 

the inspection in accordance with the 

instructions of this SB. 

For the reasons described above, this 

[EASA] AD, which supersedes DGAC France 

AD F–2005–108, requires a one-time 

inspection (improved method) to identify the 

type of MFLI installed and, depending on 

findings, replacement or repair, as 

applicable. This [EASA] AD also prohibits 

the installation of the affected MFLI on any 

aeroplane as replacement parts. 

The repair may also include locating 

and removing any missing top stop, and 

inspecting for any damage caused to the 

fuel tank by a missing top stop. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–28–1209, dated December 12, 

2011. 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 


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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 

Where the MCAI states in the 

compliance time ‘‘whichever occurs 

later,’’ this proposed AD would require 

‘‘whichever occurs earlier.’’ We have 

determined that this compliance time 

would address the unsafe condition in 

a more timely manner. We considered 

the manufacturer’s recommendation, 

and the overall risk to the fleet, 

including the severity of the failure and 

the likelihood of the failure’s 

occurrence. Therefore, we find that a 

compliance time of 49,000 flight hours 

after May 1, 2006, or at the next 

scheduled fuel tank entry after the 

effective date of this AD, whichever 

occurs first, to complete the required 

actions to be warranted. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 755 products of U.S. 

registry. 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Parts numbers review [retained actions 

from AD 2006–06–14, Amendment 39– 

14523 (71 FR 15023, March 27, 2006)].

Between 1 and 8 

work-hours × $85 

per hour = Between $85 and 

$680.

None ...... Between $85 and 

$680.

Between $64,175 and $513,400 

Inspection for part numbers [new proposed action].21 work-hours × 

$85 per hour = 

$1,785.

$0 ........... $1,785 .................... $1,347,675 

We estimate the following costs to do 

any necessary replacement or repair that 

would be required based on the results 

of the proposed inspection. We have no 

way of determining the number of 

aircraft that might need the replacement 

or repair: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace or repair .......................................................... 4 work-hours × $85 per hour = $340 ........................... $0 $340 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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 proposed 

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 

removing airworthiness directive (AD) 

2006–06–14, Amendment 39–14523 (71 

FR 15023, March 27, 2006), and adding 

the following new AD: 

Airbus: Docket No. FAA–2013–0698; 

Directorate Identifier 2012–NM–136–AD. 

(a) Comments Due Date 

We must receive comments by October 4, 

2013. 


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(b) Affected ADs 

This AD supersedes AD 2006–06–14, 

Amendment 39–14523 (71 FR 15023, March 

27, 2006). 

(c) Applicability 

This AD applies to Airbus Model A318– 

111, A318–112, A318–121, A318–122, A319– 

111, A319–112, A319–113, A319–114, A319– 

115, A319–131, A319–132, A319–133, A320– 

111, A320–211, A320–212, A320–214, A320– 

215, A320–216, A320–231, A320–232, A320– 

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

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

A321–232 airplanes; certificated in any 

category; all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28: Fuel. 

(e) Reason 

This AD was prompted by a report of 

several in-service incidents of wear and 

detachment of the top-stops from magnetic 

fuel level indicators (MFLI) in a wing fuel 

tank. We are issuing this AD to prevent an 

ignition source in the wing fuel tank in the 

event of a lighting strike, which could result 

in a fire or explosion. 

(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 Review of Airplane 

Maintenance Records/Investigative and 

Corrective Actions 

This paragraph restates the requirements of 

paragraph (f) of AD 2006–06–14, Amendment 

39–14523 (71 FR 15023, March 27, 2006). For 

Model A318–111 and –112 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; A320–111 

airplanes; Model A320–211, –212, –214, 

–231, –232, and –233 airplanes; Model 

A321–111, –112, and –131 airplanes; and 

Model A321–211, –212, –213, –231, and –232 

airplanes; on which Airbus Modification 

27496 has not been installed in production: 

Within 65 months or 6,500 flight hours after 

May 1, 2006 (the effective date of AD 2006– 

06–14), whichever is first, review the 

airplane’s maintenance records to determine 

the part number (P/N) of each MFLI of the 

wing fuel tanks in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–28–1138, dated March 

18, 2005. If the P/N cannot be identified, or 

the P/N is identified in the ‘‘old P/N’’ column 

of the table in paragraph 1.L., 

‘‘Interchangeability/Mixability,’’ of Airbus 

Service Bulletin A320–28–1138, dated March 

18, 2005, before further flight, do the 

applicable related investigative and 

corrective actions by accomplishing all of the 

actions in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–28–1138, dated March 

18, 2005. 

(h) Retained Parts Installation Prohibition 

This paragraph restates the requirements 

paragraph (g) of AD 2006–06–14, 

Amendment 39–14523 (71 FR 15023, March 

27, 2006). For Model A318–111 and –112 

airplanes; Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes; 

A320–111 airplanes; Model A320–211, –212, 

–214, –231, –232, and –233 airplanes; Model 

A321–111, –112, and –131 airplanes; and 

Model A321–211, –212, –213, –231, and –232 

airplanes; on which Airbus Modification 

27496 has not been installed in production: 

As of May 1, 2006 (the effective date of AD 

2006–06–14), no person may install on any 

airplane any MFLI of the wing fuel tanks 

with a P/N identified in the ‘‘old P/N’’ 

column of the table in paragraph 1.L., 

‘‘Interchangeability/Mixability,’’ of Airbus 

Service Bulletin A320–28–1138, dated March 

18, 2005. 

(i) New Requirement of This AD: Inspection 

For all airplanes, except as provided by 

paragraph (k) of this AD: At the next 

scheduled fuel tank entry after the effective 

date of this AD, or within 49,000 flight hours 

after May 1, 2006 (the effective date of AD 

2006–06–14, Amendment 39–14523 (71 FR 

15023, March 27, 2006), whichever occurs 

first, perform a special detailed inspection of 

the wing tank to determine which type of 

magnetic fuel level indicators (MFLI) are 

installed, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–28–1209, dated 

December 12, 2011. A review of airplane 

maintenance records is acceptable in lieu of 

this inspection, if the part number and the 

type of the installed MFLI can be 

conclusively determined from that review. 

Paragraphs (i)(1) through (i)(11) of this AD 

identify the affected MLFI part numbers. 

(1) 3508802–24 

(2) 3508802–25 

(3) 3508802–26 

(4) 3508802–27 

(5) 3508802–28 

(6) 3508802–34 

(7) 3508802–39 

(8) 3508802–74 

(9) 3508802–75 

(10) 3508802–76 

(11) 3508802–91 

Note 1 to paragraph (i) of this AD: The 

affected MFLI have the ‘S’-shaped lock-wire 

design. 

(j) New Requirement of This AD: 

Replacement or Repair 

If, during the inspection required by 

paragraph (i) of this AD, a MFLI with the ‘S’ 

shaped lock-wire design (Part Number (P/N) 

listed in paragraphs (i)(1) through (i)(11) of 

this AD) is found, then at the next scheduled 

fuel tank entry after the effective date of this 

AD, or within 49,000 flight hours after May 

1, 2006 (the effective date of AD 2006–06–14, 

Amendment 39–14523 (71 FR 15023, March 

27, 2006), whichever occurs first, replace the 

affected MFLI with a serviceable part and 

accomplish the corrective actions (repair), as 

applicable, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–28–1209, dated 

December 12, 2011. For the purpose of this 

AD, a serviceable part is a composite MFLI, 

or a metallic MFLI with the top stop retained 

by a ‘trapped wire,’ as applicable to the 

location identified in Table 1 of paragraph (j) 

of this AD. 

TABLE 1 OF PARAGRAPH (J) OF THIS

AD—METALLIC MFLI WITH THE TOP

STOP RETAINED BY A ‘TRAPPED

WIRE,’ INCLUDING APPLICABLE LOCATION (FIN) 

MFLI P/N Applicable location (FIN) 

3508802–35 56/57QM 

3508802–36 58/59QM 

3508802–37 60/61QM 

3508802–38 62/63QM 

(k) New Requirement of This AD: Exception 

for Paragraph (i) of This AD 

Airplanes on which Airbus modification 

(mod) 27496 has been embodied in 

production, and on which no wing tank 

MFLI replacement with a part number listed 

in paragraph (i)(1) through (i)(11) of this AD 

has been made since first flight, are not 

affected by the requirement of paragraph (i) 

of this AD. 

(l) New Requirement of This AD: Parts 

Installation Prohibition 

As of the effective date of this AD, do not 

install on any airplane a MFLI with a part 

number listed in paragraph (i)(1) through 

(i)(11) of this AD. 

(m) 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1405; fax (425) 227– 

1149. Information may be emailed to: M-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 its delegated agent, or by the Design 

Approval Holder with a State of Design 

Authority’s design organization approval). 

For a repair method to be approved, the 

repair approval must specifically refer to this 

AD. You are required to assure the product 

is airworthy before it is returned to service. 

(n) Special Flight Permits 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 


sroberts on DSK5SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Proposed Rules 51121 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2012–0119, dated 

July 4, 2012, for related information, which 

can be found in the AD docket on the 

Internet at http://www.regulations.gov. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; 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 August 

9, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–20251 Filed 8–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0742; Directorate 

Identifier 2013–CE–012–AD] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. 

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 Piper Aircraft, 

Inc. Models PA–28–140, PA–28–150, 

PA–28–160, PA–28–180, PA–28R–180, 

and PA–28R–200 airplanes. AD 71–21– 

08, Amendment 39–1312 (36 FR 19572, 

October 8, 1971) currently requires 

replacement of the fuel selector valve 

cover. Since we issued AD 71–21–08, it 

has been found that a similar fuel 

selector valve issue exists in additional 

serial numbered airplanes not identified 

in the existing AD. This proposed AD 

would add additional airplanes to the 

AD’s applicability section and changes 

the compliance time of the required 

actions. We are proposing this AD to 

correct the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by October 4, 2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Piper Aircraft, Inc., 

2926 Piper Drive, Vero Beach, Florida 

32960; telephone: (772) 567–4361; fax: 

(772) 978–6573; email: 

customer.service@piper.com; Internet: 

www.piper.com/home/pages/

Publications.cfm. You may review 

copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; or in person at the 

Docket Management Facility 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 Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Gary 

Wechsler, Aerospace Engineer, Atlanta 

Aircraft Certification Office, FAA, 1701 

Columbia Avenue, College Park, Georgia 

30337; telephone: (404) 474–5575; fax: 

(404) 474–5606; email: gary.wechsler@

faa.gov. 

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–2013–0742; Directorate Identifier 

2013–CE–012–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 because of 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 September 29, 1971, we issued AD 

71–21–08, Amendment 39–1312 (36 FR 

19572, October 8, 1971), for certain 

Piper Aircraft, Inc. Models PA–28–140, 

PA–28–180, PA–28R–180, and PA–28R– 

200 airplanes. That AD requires a 

replacement of the fuel selector valve 

cover to prevent possible binding of the 

fuel selector handle. 

Actions Since Existing AD Was Issued 

Since we issued AD 71–21–08, 

Amendment 39–1312 (36 FR 19572, 

October 8, 1971), a safety event in 2011 

caused the loss of a Model PA–28–180C 

airplane and the serious injury to one 

occupant. A subsequent FAA 

investigation revealed eight additional 

PA–28 series events dating from 1999 to 

the present were the result of a similar 

fuel selector valve assembly issue. 

Additionally, the FAA was unable to 

determine and locate records of 

notification when Piper Service Letter 

(SL) 590, dated May 25, 1972, and Piper 

Service Bulletin (SB) 840, dated June 19, 

1986, were released indicating a similar 

fuel selector valve issue existed in 

additional serial numbered airplanes 

not identified in AD 71–21–08. 

Although reliable FAA records do not 

exist for events prior to 1995, it is likely 

that the AD and Piper service 

information referenced above was 

released due to the frequency of similar 

events occurring during the periods in 

which the documents were released. 

Piper has indicated the majority of the 

airplanes added to the applicability of 

this NPRM have likely already complied 

with the proposed action. 

Relevant Service Information 

The 2011 safety event prompted us to 

review the Piper Aircraft, Inc. service 

information history, specifically Piper 

Mandatory Service Bulletin No. 840, 

dated June 19, 1986. The service 

information describes applicability and 

where to find procedures for 

replacement of the fuel selector valve 

cover. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 


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