68688 Federal Register / Vol. 78, No. 221 / Friday, November 15, 2013 / Rules and Regulations 

operated as before the change under 

VMC, safety in relation to lightning 

effects is not diminished by installing a 

‘‘glass cockpit’’. An operation in IMC, 

which would to our mind require a 

lightning protection system in 

accordance with FAR 23.867(c), is not 

considered and not permitted (reference 

AFM). For these reasons AQUILA 

proposes to remove the added 

requirement 14 CFR 23.867 from the 

Airworthiness Design Standards as 

listed in the NPRM. 

The FAA agrees with the commenter 

and has removed the added design 

criteria of 14 CFR part 23.867 at 

amendment 23–49. The final applicable 

design criteria for the installation of 

advanced avionic displays on the 

Aquila AT01–100 are the addition four 

14 CFR part 23 regulations as shown 

above. 

Applicability 

As discussed above, these 

airworthiness design standards under 

the special class, JAR–VLA rule are 

applicable to the Aquila AT01–100 

model and future JAR–VLA (CS–VLA) 

models on FAA TCDS A51CE. 

Conclusion 

This action affects only certain 

airworthiness design standards on 

Aquila AT01–100 model and future 

JAR–VLA model airplanes shown on 

FAA TCDS A51CE. It is not a standard 

of general applicability and it affects 

only the applicant who applied to the 

FAA for approval of these features on 

the airplane. 

Citation 

The authority citation for these 

airworthiness standards is as follows: 

Authority: 49 U.S.C. 106(g), 40113 and 

44701. 

Issued in Kansas City, Missouri on October 

28, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–26910 Filed 11–14–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0870; Directorate 

Identifier 2013–NM– 166–AD; Amendment 

39–17657; AD 2013–23–02] 

RIN 2120–AA64 

Airworthiness Directives; EADS CASA 

(Type Certificate Previously Held by 

Construcciones Aeronauticas, S.A.) 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

EADS CASA (Type Certificate 

previously held by Construcciones 

Aeronauticas, S.A.) Model CN–235, CN– 

235–100, CN–235–200, CN–235–300, 

and C–295 airplanes. This AD requires 

inspection of the feeder cables of certain 

fuel booster pumps for damage 

(including, but not limited to, signs of 

electrical arcing and fuel leaks), and 

replacement if necessary. This AD was 

prompted by a report of an in-flight 

problem with the fuel transfer system. 

We are issuing this AD to detect and 

correct damage to certain fuel booster 

pumps, which could create an ignition 

source in the fuel tank vapor space, and 

result in a fuel tank explosion and 

consequent loss of the airplane. 

DATES: This AD becomes effective 

December 2, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 2, 2013. 

We must receive comments on this 

AD by December 30, 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 AD, contact EADS CASA, Military 

Transport Aircraft Division (MTAD), 

Integrated Customer Services (ICS), 

Technical Services, Avenida de Arago ́n 

404, 28022 Madrid, Spain; telephone 

+34 91 585 55 84; fax +34 91 585 55 05; 

email MTA.TechnicalService@

casa.eads.net; Internet http:// 

www.eads.net. You may view this 

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 Management Facility office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this 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: 

Shahram Daneshmandi, Aerospace 

Engineer, International Branch, ANM– 

116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; telephone (425) 227– 

1112; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

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 2013–0186, 

dated August 16, 2013 (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: 

An occurrence with a CN–235 aeroplane 

has been reported, involving an in-flight 

problem with the fuel transfer system. 

The results of the subsequent investigation 

revealed damage on the fuel booster pump 

electrical feeding cable and some burn marks 

on the pump body and plate (fairing) at the 

external side of the fuel tank; confirmed 

electrical arcing between the wire and pump 

body; and revealed as well fuel leakage onto 

the affected wire. 

This condition, if not detected and 

corrected, could create an ignition source in 

the fuel tank vapour space, possibly resulting 

in a fuel tank explosion and loss of the 

aeroplane. 

To address this potential unsafe condition, 

EADS CASA (Airbus Military) issued All 

Operators Letter (AOL) 235–025 and AOL 


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Federal Register / Vol. 78, No. 221 / Friday, November 15, 2013 / Rules and Regulations 68689 

295–025, providing inspection instructions 

for the affected fuel booster pumps, Part 

Number (P/N) 1C12–34 and P/N 1C12–46. 

For the reasons described above, this 

[EASA] AD requires a one-time [detail visual] 

inspection of the affected fuel booster pumps 

to detect damage [including, but not limited, 

to signs of electrical arcing and fuel leaks] 

and, depending on findings, replacement of 

the fuel booster pump. This [EASA] AD also 

requires the reporting of all findings to EADS 

CASA for evaluation. 

This [EASA] AD is considered to be an 

interim action and further AD action may 

follow. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating it in 

Docket No. FAA–2013–0870. 

Relevant Service Information 

Airbus Military (EADS CASA) has 

issued the following service 

information. 

• For Model CN–235 airplanes: 

Airbus Military All Operator Letter 235– 

025, dated July 29, 2013. 

• For Model C–295 airplanes: Airbus 

Military All Operator Letter 295–025, 

Revision 01, dated August 1, 2013. 

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 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 issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because damage to the fuel booster 

pump could create an ignition source in 

the fuel tank vapor space, which could 

result in a fuel tank explosion and 

consequent loss of the airplane. 

Therefore, we determined that notice 

and opportunity for public comment 

before issuing this AD are impracticable 

and that good cause exists for making 

this amendment effective in fewer than 

30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2013–0870; 

Directorate Identifier 2013–NM–166– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 

Costs of Compliance 

We estimate that this AD affects 35 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

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

operators 

Inspection of fuel boost 

pump.

2 work-hours × $85 per hour = $170 per fuel boost 

pump.

$0 $170 per fuel boost pump $11,900 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need this replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Replacement of fuel boost pump .............................. 3 work-hours × $85 per hour = $255 per pump ...... $16,080 $16,335 per pump. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to 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 control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is 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. 

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 


emcdonald on DSK67QTVN1PROD with RULES
68690 Federal Register / Vol. 78, No. 221 / Friday, November 15, 2013 / Rules and Regulations 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2013–23–02 EADS CASA (Type Certificate 

Previously Held by Construcciones 

Aeronauticas, S.A.): Amendment 39– 

17657. Docket No. FAA–2013–0870; 

Directorate Identifier 2013–NM–166–AD. 

(a) Effective Date 

This AD becomes effective December 2, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to EADS CASA (Type 

Certificate previously held by Construcciones 

Aeronauticas, S.A.) Model CN–235, CN–235– 

100, CN–235–200, CN–235–300, and C–295 

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 an 

in-flight problem with the fuel transfer 

system. We are issuing this AD to detect and 

correct damage to certain fuel booster pumps, 

which could create an ignition source in the 

fuel tank vapor space, and result in a fuel 

tank explosion and consequent loss of 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 of the Feeder Cables of Certain 

Fuel Booster Pumps 

Within the times specified in paragraph 

(g)(1) or (g)(2) of this AD, as applicable: 

Perform a detailed visual inspection for 

damage (including, but not limited to, signs 

of electrical arcing and fuel leaks) of the 

electrical feeder cables of each fuel booster 

pump having part number (P/N) 1C12–34 or 

1C12–46, in accordance with the instructions 

of Airbus Military All Operator Letter 235– 

025, dated July 29, 2013 (for Model CN–235 

airplanes); or Airbus Military All Operator 

Letter 295–025, Revision 01, dated August 1, 

2013 (for Model C–295 airplanes). 

(1) For each fuel booster pump that has not 

been replaced as of the effective date of this 

AD: Prior to the accumulation of 300 total 

flight hours or within 5 cycles after the 

effective date of this AD, whichever occurs 

later. 

(2) For each fuel booster pump that has 

been replaced as of the effective date of this 

AD: Within 300 flight hours since the most 

recent fuel booster pump replacement, or 

within 5 flight cycles after the effective date 

of this AD, whichever occurs later. 

(h) Replacement of Affected Fuel Boost 

Pumps 

If any damage (including, but not limited 

to, signs of electrical arcing and fuel leaks) 

is found during the inspection required by 

paragraph (g) of this AD: Within the time 

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

AD, replace the affected fuel booster pump 

with a serviceable pump, in accordance with 

Airbus Military All Operator Letter 235–025, 

dated July 29, 2013 (for Model CN–235 

airplanes); or Airbus Military All Operator 

Letter 295–025, Revision 01, dated August 1, 

2013 (for Model C–295 airplanes). 

(1) Before further flight. 

(2) Within 10 days following the 

inspection, provided that the airplane is 

operated under the conditions specified in 

Airbus Military All Operator Letter 235–025, 

dated July 29, 2013 (for Model CN–235 

airplanes); or Airbus Military All Operator 

Letter 295–025, Revision 01, dated August 1, 

2013 (for Model C–295 airplanes). 

(i) Report of Inspection Findings 

At the applicable time specified in 

paragraph (i)(1) or (i)(2) of this AD, submit 

an inspection report to EADS CASA (Airbus 

Military), in accordance with Airbus Military 

All Operator Letter 235–025, dated July 29, 

2013 (for Model CN–235 airplanes); or Airbus 

Military All Operator Letter 295–025, 

Revision 01, dated August 1, 2013 (for Model 

C–295 airplanes). 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 10 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 10 days after the effective date of this 

AD. 

(j) 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: 

Shahram Daneshmandi, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (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, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or by the Design 

Approval Holder (DAH) 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 ensure 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, 


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Federal Register / Vol. 78, No. 221 / Friday, November 15, 2013 / Rules and Regulations 68691 

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. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0186, dated August 16, 2013, 

for related information. You may examine the 

MCAI in the AD docket on the Internet at 

http://www.regulations.gov by searching for 

and locating it in Docket No. FAA–2013– 

0870. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Military All Operator Letter 235– 

025, dated July 29, 2013. 

(ii) Airbus Military All Operator Letter 

295–025, Revision 01, dated August 1, 2013. 

(3) For service information identified in 

this AD, contact EADS–CASA, Military 

Transport Aircraft Division (MTAD), 

Integrated Customer Services (ICS), 

Technical Services, Avenida de Arago ́n 404, 

28022 Madrid, Spain; telephone +34 91 585 

55 84; fax +34 91 585 55 05; email 

MTA.TechnicalService@casa.eads.net; 

Internet http://www.eads.net. 

(4) You may view this 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on October 

31, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–27017 Filed 11–14–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0630; Directorate 

Identifier 2012–NM–213–AD; Amendment 

39–17660; AD 2013–23–05] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Fokker Services B.V. Model F.28 Mark 

0070 and 0100 airplanes. This AD was 

prompted by a design review, which 

revealed that, under certain failure 

conditions, wiring in the main fuel tank 

could develop a short circuit that might 

cause a hot spot on the wiring conduit 

or puncture the wiring conduit wall. 

This AD requires installing fuses in the 

power supply wiring and/or return 

wiring for various components in the 

fuel system; and revising the airplane 

maintenance program by incorporating 

critical design configuration control 

limitations. We are issuing this AD to 

prevent an ignition source in the main 

fuel tank vapor space, which could 

result in a fuel tank explosion and 

consequent loss of the airplane. 

DATES: This AD becomes effective 

December 20, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 20, 2013. 

ADDRESSES: You may examine the AD 

on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0630; or in 

person at the U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC. 

For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 

1357, 2130 EL Hoofddorp, the 

Netherlands; telephone +31 (0)88–6280– 

350; fax +31 (0)88–6280–111; email 

technicalservices@fokker.com; Internet 

http://www.myfokkerfleet.com. You may 

view this 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. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on July 31, 2013 (78 FR 46303). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0241, 

dated November 12, 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: 

Prompted by an accident * * *, the FAA 

published Special Federal Aviation 

Regulation (SFAR) 88 [66 FR 23086, May 7, 

2001], and the Joint Aviation Authorities 

(JAA) published Interim Policy INT/POL/25/ 

12. 

The design review conducted by Fokker 

Services on the Fokker 70 and Fokker 100 in 

response to these regulations revealed that 

under certain failure conditions of the wiring 

of the Overflow Valve Reed Switch, or the 

solenoid of the Level Control Pilot Valve 

(LCPV), or the solenoid of the Re/De-fueling 

Shut- Off Valve, or the Collector-Tank Low 

Level Float-Switch, a short circuit may 

develop that causes a hot spot on the wiring 

conduit, or puncturing of the wiring conduit 

wall in the main fuel tank. 

This condition, if not corrected, could 

create an ignition source in the main fuel 

tank vapour space, possibly resulting in a 

fuel tank explosion and consequent loss of 

the aeroplane. 

For the reasons described above, this 

[EASA]AD requires the installation of fuses 

in the power supply wiring and/or return 

wiring for the main tank overflow valve reedswitches, the LCPV solenoid, the Re/De-fuel 

shut-off valve solenoid and the collector-tank 

Low Level float switch and subsequently, the 

implementation of the associated Critical 

Design Configuration Control Limitations 

(CDCCL[s]) [and revising the maintenance 

program to incorporate the CDCCLs]. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0630- 

0002. 


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