34 Federal Register / Vol. 81, No. 1 / Monday, January 4, 2016 / Proposed Rules 

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. 

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): 

Bombardier, Inc.: Docket No. FAA–2015– 

8129; Directorate Identifier 2014–NM– 

197–AD. 

(a) Comments Due Date 

We must receive comments by February 

18, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2B16 (CL–604 Variant) airplanes, 

certificated in any category, serial numbers 

5301 through 5665 inclusive, and 5701 

through 5962 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by a determination 

that certain maintenance tasks for the 

horizontal stabilizer trim actuator (HSTA) are 

inadequate. We are issuing this AD to detect 

and correct premature wear and cracking of 

the HSTA, which could result in failure of 

the HSTA and consequent loss of control of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Maintenance or Inspection Program 

Revision 

Within 30 days after the effective date of 

this AD: Revise the maintenance or 

inspection program, as applicable, to 

incorporate Task 27–42–01–109, Restoration 

(Overhaul) of the Horizontal Stabilizer Trim 

Actuator, Part No. 604–92305–7 and Subs 

(Vendor Part No. 8454–3 and Subs); and Task 

27–42–01–111, Detailed Inspection of the 

Horizontal Trim Actuator (HSTA) Secondary 

Load Path Indicator, Part No. 604–92305–7 

and Subs (Vendor Part No. 8454–3 and Subs); 

of the applicable document identified in 

paragraph (g)(1) or (g)(2) of this AD. 

(1) For Model CL–600–2B16 (CL–604 

Variant) airplanes, serial numbers 5301 

through 5665 inclusive: Section 5–10–40, 

Certification Maintenance Requirements, of 

Part 2, Airworthiness Limitations, Revision 

22, dated July 11, 2014, of the Bombardier 

Challenger 604 Time Limits/Maintenance 

Checks Manual. 

(2) For Model CL–600–2B16 (CL–604 

Variant) airplanes, serial numbers 5701 

through 5962 inclusive: Section 5–10–40, 

Certification Maintenance Requirements, of 

Part 2, Airworthiness Limitations, Revision 

10, dated July 11, 2014, of the Bombardier 

Challenger 605 Time Limits/Maintenance 

Checks Manual. 

(h) No Alternative Actions or Intervals 

After the maintenance or inspection 

program has been revised, as required by 

paragraph (g) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (i)(1) of 

this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

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) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, ANE–170, 

FAA; or Transport Canada Civil Aviation 

(TCCA); or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–30, dated 

September 5, 2014, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2015–8129. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. You may view this 

service information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue SW., 

Renton, WA. 

Issued in Renton, Washington, on 

December 18, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–32888 Filed 12–31–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8138; Directorate 

Identifier 2014–NM–112–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2011–17– 

10 for all Fokker Services B.V. Model 

F.28 Mark 1000, 2000, 3000, and 4000 

airplanes. AD 2011–17–10 currently 

requires inspecting for a by-pass wire 

between the housing of each in-tank fuel 

quantity indication (FQI) cable plug and 

the cable shield, and corrective actions 

if necessary. AD 2011–17–10 also 

requires revising the airplane 

maintenance program. Since we issued 

AD 2011–17–10, revised service 

information has been issued to update 

the critical design configuration control 

limitations (CDCCLs) that address 

potential ignition sources inside fuel 

tanks. This proposed AD would require 

revising the airplane maintenance or 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 1 / Monday, January 4, 2016 / Proposed Rules 35 

inspection program by incorporating the 

instructions in the revised service 

information. The proposed AD also 

removes certain airplanes from the 

applicability. We are proposing this AD 

to prevent potential ignition sources 

inside the fuel tanks, which, in 

combination with flammable fuel 

vapors, could result in fuel tank 

explosions and consequent loss of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by February 18, 2016. 

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: 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 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

8138; 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 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, WA 

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–2015–8138; Directorate Identifier 

2014–NM–112–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 August 3, 2011, we issued AD 

2011–17–10, Amendment 39–16774 (76 

FR 50111, August 12, 2011), for all 

Model F.28 Mark 1000, 2000, 3000, and 

4000 airplanes. AD 2011–17–10 requires 

inspecting for a by-pass wire between 

the housing of each in-tank FQI cable 

plug and the cable shield and corrective 

actions (installing a by-pass wire) if 

necessary. AD 2011–17–10 also requires 

revising the airplane maintenance 

program. 

Since we issued AD 2011–17–10, 

Amendment 39–16774 (76 FR 50111, 

August 12, 2011), revised service 

information has been issued to update 

the critical CDCCLs that address 

potential ignition sources inside fuel 

tanks. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0111, dated May 8, 2014 

(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: 

* * * [T]he FAA published Special 

Federal Aviation Regulation (SFAR) 88, and 

the Joint Aviation Authorities (JAA) 

published Interim Policy INT/POL/25/12. 

The review conducted by Fokker Services 

on the F28 design, in response to these 

regulations, revealed that on certain 

aeroplanes, an interrupted shield contact 

may exist or develop between the housing of 

an in-tank Fuel Quantity Indication (FQI) 

cable plug and the cable shield of the 

shielded FQI system cables in the main and 

collector fuel tanks, which can, under certain 

conditions, form a spark gap. 

This condition, if not detected and 

corrected, may create an ignition source in 

the fuel tank vapour space, possibly resulting 

in a wing fuel tank explosion and consequent 

loss of the aeroplane. 

To address and correct this unsafe 

condition, Fokker Services published Service 

Bulletin (SB) SBF28–28–053 which provides 

instructions, for early production aeroplanes, 

for a one-time inspection to check for the 

presence of a by-pass wire between the 

housing of each in-tank FQI cable plug and 

the cable shield and, depending on findings, 

for the installation of a by-pass wire. In 

addition, SBF28–28–053 provides a Critical 

Design Configuration Control Limitation 

(CDCCL) item to make certain that the bypass wire remains installed on these 

aeroplanes. 

On later production aeroplanes, an 

improved plug Part Number (P/N) 20P227–2 

was introduced with a better shield 

connection to the housing of the plug. 

Therefore, SBF28–28–053 (original issue and 

Revision 1) also provided a CDCCL item to 

ensure that this type of plug remains 

installed on those aeroplanes. 

EASA issued AD 2010–0217 [which 

corresponds to FAA AD 2011–17–10, 

Amendment 39–16774 (76 FR 50111, August 

12, 2011)] to require accomplishment of the 

instructions related to the by-pass wire and 

implementation of the CDCCL items as 

specified in Fokker Services SBF28–28–053 

Revision 1, as applicable to aeroplane s/n. 

Since EASA AD 2010–0217 was issued, it 

was identified that P/N 20P227–2 and 

20P228–1 plugs are also approved and can 

therefore be installed on the later production 

aeroplanes. Prompted by this finding, Fokker 

Services issued SBF28–28–055 to address the 

implementation of a CDCCL item to make 

certain that only approved plug types remain 

installed on the later production aeroplanes, 

while SBF28–28–053 Revision 2 was issued 

for early production aeroplanes to address 

the by-pass wire related actions only. 

Consequently, EASA issued AD 2011– 

0184, retaining the requirements of EASA AD 

2010–0217, which was superseded, to require 

implementation of the related CDCCL items 

as specified in Fokker Services SBF28–28– 

053 Revision 2, or SBF28–28–055, as 

applicable to aeroplane s/n. 

More recently, Fokker Services published 

Revision 3 of SBF28–28–053, to eliminate the 

use of a heat gun in or near to the fuel tank, 

and prompted by a change to the definition 

of the related CDCCL item. Fokker Services 

also cancelled SBF28–28–055, due to the 

introduction of a revised definition of the 

CDCCL item that has been published in 

Fokker Services SBF28–28–050, Revision 2. 

For the reason described above, this 

[EASA] AD retains the requirements related 

to SBF28–28–053 of EASA AD 2011–0184, 

which is superseded, but requires those 

actions to be accomplished in accordance 

with the instructions of Fokker Services 

SBF28–28–053, Revision 3 (R3). 

All the actions related to SBF28–28–055, as 

previously required through paragraphs (5) 


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and (6) of EASA AD 2011–0184, are now 

addressed by EASA AD 2014–0110 [http://

ad.easa.europa.eu/ad/2014-0110] which has 

been superseded by EASA AD 2015–0030 

[http://ad.easa.europa.eu/ad/2015-0030]. 

* * * * * 

The CDCCL requirement in AD 2011– 

17–10, Amendment 39–16774 (76 FR 

50111, August 12, 2011) for Model F.28 

Mark 2000, 3000, and 4000 airplanes is 

now addressed in other related 

rulemaking. Therefore this proposed AD 

does not include Model F.28 Mark 2000, 

3000, and 4000 airplanes in the 

applicability. 

This AD also removes airplanes 

having serial numbers 11993 and 19994 

from the applicability because those 

airplanes were scrapped and removed 

from the type certificate data sheet. 

The unsafe condition is the potential 

of ignition sources inside fuel tanks. 

Such ignition sources, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. 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–2015–8138. 

Related Service Information Under 1 

CFR Part 51 

Fokker Services B.V. has issued 

Fokker Service Bulletin SBF28–28–053, 

Revision 3, dated January 9, 2014. The 

service information describes 

procedures for inspecting for a by-pass 

wire between the housing of each intank FQI cable plug and the cable 

shield, and installing a by-pass wire if 

necessary. The service information also 

describes CDCCL item 1.7 for fuel 

quantity indicating system (FQIS) 

wiring in wing tanks. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section of this NPRM. 

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. 

This proposed AD would require 

implementation of certain maintenance 

requirements and airworthiness 

limitations. This proposed AD would 

also require accomplishing the actions 

specified in the service information 

described previously. 

This proposed AD would require 

revisions to certain operator 

maintenance documents to include new 

actions (e.g., inspections) and CDCCLs. 

Compliance with these actions and 

CDCCLs is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired 

in the areas addressed by these actions, 

the operator may not be able to 

accomplish the actions described in the 

revisions. In this situation, to comply 

with 14 CFR 91.403(c), the operator 

must request approval for an alternative 

method of compliance according to the 

procedures specified in paragraph (n)(1) 

of this AD. The request should include 

a description of changes to the required 

actions that will ensure the continued 

operational safety of the airplane. 

Notwithstanding any other 

maintenance or operational 

requirements, components that have 

been identified as airworthy or installed 

on the affected airplanes before 

accomplishing the revision of the 

airplane maintenance or inspection 

program specified in this AD, do not 

need to be reworked in accordance with 

the CDCCLs. However, once the airplane 

maintenance or inspection program has 

been revised as required by this AD, 

future maintenance actions on these 

components must be done in 

accordance with the CDCCLs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 5 airplanes of U.S. registry. This 

proposed AD would merely require 

using the Accomplishment Instructions 

in the revised service information. The 

current costs associated with this 

proposed AD are repeated as follows for 

the convenience of affected operators: 

The actions that are required by AD 

2011–17–10, Amendment 39–16774 (76 

FR 50111, August 12, 2011), will take 

about 6 work-hours per product, at an 

average labor rate of $85 per work-hour. 

Required parts cost about $0 per 

product. Based on these figures, the 

estimated cost of the actions that were 

required by AD 2011–17–10 is $510 per 

product. 

In addition, we estimate that any 

necessary follow-on actions required by 

AD 2011–17–10 will take about 7 workhours and require parts costing $308, for 

a cost of $903 per product. We have no 

way of determining the number of 

products that may need these actions. 

We also estimate that it would take 

about 1 work-hour per product to revise 

the maintenance or inspection program 

in this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $425, or $85 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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. 

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: 


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Federal Register / Vol. 81, No. 1 / Monday, January 4, 2016 / Proposed Rules 37 

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) 

2011–17–10, Amendment 39–16774 (76 

FR 50111, August 12, 2011), and adding 

the following new AD: 

Fokker Services B.V.: Docket No. FAA– 

2015–8138; Directorate Identifier 2014–NM– 

112–AD. 

(a) Comments Due Date 

We must receive comments by February 

18, 2016. 

(b) Affected ADs 

This AD replaces AD 2011–17–10, 

Amendment 39–16774 (76 FR 50111, August 

12, 2011). 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F.28 Mark 1000 airplanes; certificated 

in any category; serial numbers (S/Ns) 11003 

through 11041 inclusive, and S/Ns 11991 and 

11992. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by the issuance of 

revised service information to update the 

critical design configuration control 

limitations (CDCCLs) that address potential 

ignition sources inside fuel tanks. We are 

issuing this AD to prevent potential ignition 

sources inside the fuel tanks, which, in 

combination with flammable fuel vapors, 

could result in fuel tank explosions and 

consequent loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection and Installation 

With Revised Service Information 

This paragraph restates the actions 

required by paragraph (g) of AD 2011–17–10, 

Amendment 39–16774 (76 FR 50111, August 

12, 2011), with revised service information. 

At a scheduled opening of the fuel tanks, but 

not later than 84 months after September 16, 

2011 (the effective date of AD 2011–17–10), 

do a general visual inspection for the 

presence of a by-pass wire between the 

housing of each in-tank fuel quantity 

indication (FQI) cable plug and the cable 

shield, in accordance with Part 1 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF28–28–053, Revision 1, 

dated September 20, 2010, or Revision 3, 

dated January 9, 2014. As of the effective date 

of this AD, only Fokker Service Bulletin 

SBF28–28–053, Revision 3, dated January 9, 

2014, may be used. 

(h) Retained Corrective Actions, With 

Revised Service Information 

This paragraph restates the actions 

required by paragraph (h) of AD 2011–17–10, 

Amendment 39–16774 (76 FR 50111, August 

12, 2011), with revised service information. 

If during the general visual inspection 

required by paragraph (g) of this AD, it is 

found that a by-pass wire is not installed: 

Before the next flight, install the by-pass wire 

between the housing of the in-tank FQI cable 

plug and the cable shield, in accordance with 

Part 2 of the Accomplishment Instructions of 

Fokker Service Bulletin SBF28–28–053, 

Revision 1, dated September 20, 2010, or 

Revision 3, dated January 9, 2014. As of the 

effective date of this AD, only Fokker Service 

Bulletin SBF28–28–053, Revision 3, dated 

January 9, 2014, may be used. 

(i) Retained Maintenance Program Revision 

To Add Fuel Airworthiness Limitation, With 

a New Exception 

This paragraph restates the actions 

required by paragraph (i) of AD 2011–17–10, 

Amendment 39–16774 (76 FR 50111, August 

12, 2011), with a new exception. Except as 

required by paragraph (k) of this AD, 

concurrently with paragraph (g) of this AD, 

revise the airplane maintenance program by 

incorporating CDCCL–1 specified in 

paragraph 1.L.(1)(c) of Fokker Service 

Bulletin SBF28–28–053 Revision 1, dated 

September 20, 2010. 

(j) Retained No Alternative Actions, 

Intervals, and/or CDCCLs Requirement, With 

a New Exception 

This paragraph restates the actions 

required by paragraph (k) of AD 2011–17–10, 

Amendment 39–16774 (76 FR 50111, August 

12, 2011), with a new exception. Except as 

required by paragraph (k) of this AD: After 

accomplishing the revision required by 

paragraph (i) of this AD, no alternative 

actions (e.g., inspection, interval) and/or 

CDCCLs may be used unless the actions, 

intervals, and/or CDCCLs are approved as an 

alternative methods of compliance (AMOC) 

in accordance with the procedures specified 

in paragraph (n)(1) of this AD. 

(k) New Maintenance or Inspection Program 

Revision To Add Fuel Airworthiness 

Limitation 

Within 30 days after the effective date of 

this AD: Revise the airplane maintenance or 

inspection program, as applicable, by 

incorporating CDCCL item 1.7 as specified in 

paragraph 1.L.(1)(c) of Fokker Service 

Bulletin SBF28–28–053, Revision 3, dated 

January 9, 2014. Accomplishing the revision 

required by this paragraph terminates the 

revision required by paragraph (i) of this AD. 

(l) No Alternative CDCCLs 

After the maintenance or inspection 

program has been revised as required by 

paragraph (k) of this AD, no alternative 

CDCCLs may be used unless the CDCCLs are 

approved as an AMOC in accordance with 

the procedures specified in paragraph (n)(1) 

of this AD. 

(m) Credit for Previous Actions 

This paragraph provides credit for the 

applicable actions required by paragraphs (k) 

of this AD, if those actions were performed 

before the effective date of this AD using 

Fokker Service Bulletin SBF28–28–053, 

Revision 2, dated June 22, 2011. 

(n) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

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. 

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. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Fokker B.V. Service’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(o) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2014–0111, dated May 8, 2014, for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

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

and locating Docket No. FAA–2015–8138. 

(2) 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. 

Issued in Renton, Washington, on 

December 21, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–32905 Filed 12–31–15; 8:45 am] 

BILLING CODE 4910–13–P 


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