This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

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the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

65121 

Vol. 80, No. 206 

Monday, October 26, 2015 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4209; Directorate 

Identifier 2015–NM–156–AD; Amendment 

39–18302; AD 2015–21–09] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2015–19– 

02 for all The Boeing Company Model 

767 airplanes. AD 2015–19–02 required 

revising the maintenance or inspection 

program to include new airworthiness 

limitations. This AD continues to 

require a maintenance or inspection 

program revision, but with revised 

language. This AD was prompted by a 

determination that certain language in 

the airworthiness limitation was not 

accurate in AD 2015–19–02. We are 

issuing this AD to detect and correct 

latent failures of the fuel shutoff valve 

to the engine and auxiliary power unit 

(APU), which could result in the 

inability to shut off fuel to the engine 

and APU and, in case of certain fires, an 

uncontrollable fire that could lead to 

structural failure. 

DATES: This AD is effective October 28, 

2015. 

We must receive any comments on 

this AD by December 10, 2015. 

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 20590, 

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

through Friday, except Federal holidays. 

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– 

4209; 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 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: 

Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6509; fax: 

425–917–6590; email: rebel.nichols@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On September 7, 2015, we issued AD 

2015–19–02, Amendment 39–18265 (80 

FR 55512, September 16, 2015), for all 

The Boeing Company Model 767 

airplanes. AD 2015–19–02 required 

revising the maintenance or inspection 

program to include new airworthiness 

limitations. AD 2015–19–02 resulted 

from reports of latently failed fuel 

shutoff valves discovered during fuel 

filter replacement. We issued AD 2015– 

19–02 to detect and correct latent 

failures of the fuel shutoff valve to the 

engine and APU, which could result in 

the inability to shut off fuel to the 

engine and APU and, in case of certain 

fires, an uncontrollable fire that could 

lead to structural failure. 

Actions Since AD 2015–19–02, 

Amendment 39–18265 (80 FR 55512, 

September 16, 2015), Was Issued 

Since we issued AD 2015–19–02, 

Amendment 39–18265 (80 FR 55512, 

September 16, 2015), we have 

determined that extraneous language 

was included in two locations of the 

text of the airworthiness limitations 

specified in AD 2015–19–02. In 

paragraph C.7.a. of the ‘‘Description’’ 

column of figure 1 to paragraph (g) of 

AD 2015–19–02, the text ‘‘or the APU 

selector switch on the overhead panel is 

in the ON position’’ is not relevant to 

the actions specified in that paragraph. 

In paragraph A.5. of the ‘‘Description’’ 

column of figure 3 to paragraph (g) of 

AD 2015–19–02, the text ‘‘the FUEL 

CONTROL switch is in the RUN 

position or’’ is not relevant to the 

actions specified in that paragraph. 

We have determined that the language 

must be corrected to avoid any 

confusion in the paragraphs of the 

airworthiness limitation. We are issuing 

this AD to detect and correct latent 

failures of the fuel shutoff valve to the 

engine and APU, which could result in 

the inability to shut off fuel to the 

engine and APU and, in case of certain 

fires, an uncontrollable fire that could 

lead to structural failure. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD requires revising the 

maintenance or inspection program to 

include new airworthiness limitations. 

Interim Action 

We consider this AD interim action. 

The manufacturer is currently 

developing a modification that will 

address the unsafe condition identified 

in this AD. Once this modification is 

developed, approved, and available, we 

might consider additional rulemaking. 

FAA’s Justification and Determination 

of the Effective Date 

We are superseding AD 2015–19–02, 

Amendment 39–18265 (80 FR 55512, 

September 16, 2015), to correct 

inaccurate terminology in the 


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65122 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations 

‘‘Description’’ column of figure 1 to 

paragraph (g) of AD 2015–19–02 and 

figure 3 to paragraph (g) of AD 2015–19– 

02. We have made no other changes to 

the requirements published in AD 

2015–19–02. We have determined that 

the changes impose no additional 

burden on any operator. Therefore, we 

find that notice and opportunity for 

prior public comment are unnecessary 

and that good cause exists for making 

this amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the Docket Number 

FAA–2015–4209 and Directorate 

Identifier 2015–NM–156–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 450 

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 

Incorporating Airworthiness Limitation ............ 1 work-hour × $85 per hour = $85 ................. $0 $85 $38,250 

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 

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 

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 part 39 of the Federal 

Aviation Regulations (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) 

2015–19–02, Amendment 39–18265 (80 

FR 55512, September 16, 2015), and 

adding the following new AD: 

2015–21–09 The Boeing Company: 

Amendment 39–18302; Docket No. 

FAA–2015–4209; Directorate Identifier 

2015–NM–156–AD. 

(a) Effective Date 

This AD is effective October 28, 2015. 

(b) Affected ADs 

This AD replaces AD 2015–19–02, 

Amendment 39–18265 (80 FR 55512, 

September 16, 2015). 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 767–200, –300, –300F, and 

–400ER series airplanes, certificated in any 

category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by reports of 

latently failed fuel shutoff valves discovered 

during fuel filter replacement. We are issuing 

this AD to detect and correct latent failures 

of the fuel shutoff valve to the engine and 

auxiliary power unit (APU), which could 

result in the inability to shut off fuel to the 

engine and APU and, in case of certain fires, 

an uncontrollable fire that could lead to 

structural failure. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revision of Maintenance or Inspection 

Program 

Within 30 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to add airworthiness 

limitation numbers 28–AWL–ENG, 28–AWL– 

MOV, and 28–AWL–APU, by incorporating 

the information specified in figure 1, figure 

2, and figure 3 to paragraph (g) of this AD 

into the Airworthiness Limitations Section of 

the Instructions for Continued Airworthiness. 

The initial compliance time for 

accomplishing the actions specified in figure 

1, figure 2, and figure 3 to paragraph (g) of 

this AD is within 10 days after accomplishing 

the maintenance or inspection program 

revision required by this paragraph. 


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FIGURE 1 TO PARAGRAPH (g) OF THIS AD: ENGINE FUEL SHUTOFF VALVE (FUEL SPAR VALVE) POSITION INDICATION

OPERATIONAL CHECK

AWL No. Task Interval Applicability Description 

28–AWL–ENG ... ALI DAILY ................................. 767–200, –300, and –300F 

airplanes.

Engine Fuel Shutoff Valve (Fuel Spar Valve) Position 

Indication Operational Check. 

INTERVAL NOTE: The 

operational check is not 

required on days when 

the airplane is not used 

in revenue service.

The check must be done 

before further flight once 

the airplane is returned to 

revenue service.

APPLICABILITY NOTE: Applies to airplanes with an 

actuator installed at the 

engine fuel spar valve 

position having part number (P/N) MA20A2027 

(S343T003–56) or P/N 

MA30A1001 (S343T003– 

66).

Concern: The fuel spar valve actuator design can result 

in airplanes operating with a failed fuel spar valve actuator that is not reported. A latently failed fuel spar 

valve actuator could prevent fuel shutoff to an engine. In the event of certain engine fires, the potential 

exists for an engine fire to be uncontrollable. 

Perform one of the following checks/inspection of the 

fuel spar valve position (unless checked by the 

flightcrew in a manner approved by the principal operations inspector): 

A. Operational Check during engine shutdown. 

1. Do an operational check of the left engine fuel spar 

valve actuator. 

a. As the L FUEL CONTROL switch on the quadrant 

control stand is moved to the CUTOFF position, 

verify the left SPAR VALVE disagreement light on 

the quadrant control stand illuminates and then goes 

off. 

b. If the test fails (light fails to illuminate), before further 

flight, repair faults as required (refer to Boeing airplane maintenance manual (AMM) 28–22–11). 

2. Do an operational check of the right engine fuel spar 

valve actuator. 

a. As the R FUEL CONTROL switch on the quadrant 

control stand is moved to the CUTOFF position, 

verify the right SPAR VALVE disagreement light on 

the quadrant control stand illuminates and then goes 

off. 

b. If the test fails (light fails to illuminate), before further 

flight, repair faults as required (refer to Boeing AMM 

28–22–11). 

B. Operational check during engine start. 

1. Do an operational check of the left engine fuel spar 

valve actuator. 

a. As the L FUEL CONTROL switch on the quadrant 

control stand is moved to the RUN (or RICH) position, verify the left SPAR VALVE disagreement light 

on the quadrant control stand illuminates and then 

goes off. 

b. If the test fails (light fails to illuminate), before further 

flight, repair faults as required (refer to Boeing AMM 

28–22–11). 

2. Do an operational check of the right engine fuel spar 

valve actuator. 

a. As the R FUEL CONTROL switch on the quadrant 

control stand is moved to the RUN (or RICH) position, verify the right SPAR VALVE disagreement light 

on the quadrant control stand illuminates and then 

goes off. 

b. If the test fails (light fails to illuminate), before further 

flight, repair faults as required (refer to Boeing AMM 

28–22–11). 

C. Operational check without engine operation. 

1. Supply electrical power to the airplane using standard practices. 

2. Make sure all fuel pump switches on the Overhead 

Panel are in the OFF position. 

3. If the auxiliary power unit (APU) is running, open and 

collar the L FWD FUEL BOOST PUMP (C00372) circuit breaker on the Main Power Distribution Panel. 

4. Make sure LEFT and RIGHT ENG FIRE switches on 

the Aft Aisle Stand are in the NORMAL (IN) position. 

5. Make sure L and R ENG START Selector Switches 

on the Overhead Panel, are in the OFF position. 

6. Do an operational check of the left engine fuel spar 

valve actuator. 


asabaliauskas on DSK5VPTVN1PROD with RULES
65124 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations 

FIGURE 1 TO PARAGRAPH (g) OF THIS AD: ENGINE FUEL SHUTOFF VALVE (FUEL SPAR VALVE) POSITION INDICATION

OPERATIONAL CHECK—Continued 

AWL No. Task Interval Applicability Description 

a. Move L FUEL CONTROL switch on the quadrant 

control stand to the RUN position and wait approximately 10 seconds. 

NOTE: It is normal under this test condition for the 

ENG VALVE disagreement light on the quadrant control stand to stay illuminated. 

b. Move L FUEL CONTROL switch on the quadrant 

control stand to the CUTOFF position. 

c. Verify the left SPAR VALVE disagreement light on 

the quadrant control stand illuminates and then goes 

off. 

d. If the test fails (light fails to illuminate), before further 

flight, repair faults as required (refer to Boeing AMM 

28–22–11). 

7. Do an operational check of the right engine fuel spar 

valve actuator. 

a. Move R FUEL CONTROL switch on the quadrant 

control stand to the RUN position and wait approximately 10 seconds once the FUEL CONTROL switch 

is in the RUN position. 

NOTE: It is normal under this test condition for the 

ENG VALVE disagreement light on the quadrant control stand to stay illuminated. 

b. Move R FUEL CONTROL switch on the quadrant 

control stand to the CUTOFF position. 

c. Verify the right SPAR VALVE disagreement light on 

the quadrant control stand illuminates and then goes 

off. 

d. If the test fails (light fails to illuminate), before further 

flight, repair faults as required (refer to Boeing AMM 

28–22–11). 

8. If the L FWD FUEL BOOST PUMP circuit breaker 

was collared in step 3, remove collar and close. 

D. Perform an inspection of the fuel spar valve actuator 

position. 

NOTE: This inspection may be most useful whenever 

the SPAR VALVE light does not function properly. 

1. Make sure the L FUEL CONTROL switch on the 

quadrant control stand is in the CUTOFF position. 

NOTE: It is not necessary to cycle the FUEL CONTROL switch to do this inspection. 

2. Inspect the left engine fuel spar valve actuator located in the left rear spar. 

NOTE: The Fuel Spar Valve actuators are located behind main gear doors on the rear spar. 

a. Verify the manual override handle on the engine fuel 

spar valve actuator is in the CLOSED position. 

b. Repair or replace any fuel spar valve actuator that is 

not in the CLOSED position (refer to Boeing AMM 

28–22–11). 

3. Make sure the R FUEL CONTROL switch on the 

quadrant control stand is in the CUTOFF position. 

NOTE: It is not necessary to cycle the FUEL CONTROL switch to do this inspection. 

4. Inspect the right engine fuel spar valve actuator located in the right rear spar. 

NOTE: The Fuel Spar Valve actuators are located behind main gear doors on the rear spar. 

a. Verify the manual override handle on the engine fuel 

spar valve actuator is in the CLOSED position. 

b. Repair or replace any fuel spar valve actuator that is 

not in the CLOSED position (refer to Boeing AMM 

28–22–11). 


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FIGURE 2 TO PARAGRAPH (G) OF THIS AD: ENGINE FUEL SHUTOFF VALVE (FUEL SPAR VALVE) ACTUATOR INSPECTION

AWL No. Task Interval Applicability Description 

28-AWL-MOV .... ALI 10 DAYS ............................ 767–400ER series airplanes.Engine Fuel Shutoff Valve (Fuel Spar Valve) Actuator 

Inspection. 

INTERVAL NOTE: The inspection is not required 

on days when the airplane is not used in revenue service.

The inspection must be 

done before further flight 

if it has been 10 or more 

calendar days since last 

inspection.

APPLICABILITY NOTE: Applies to airplanes with an 

actuator installed at the 

engine fuel spar valve 

position having part number (P/N) MA20A2027 

(S343T003–56) or P/N 

MA30A1001 (S343T003– 

66).

Concern: The fuel spar valve actuator design can result 

in airplanes operating with a failed fuel spar valve actuator that is not reported. A latently failed fuel spar 

valve actuator would prevent fuel shutoff to an engine. In the event of certain engine fires, the potential 

exists for an engine fire to be uncontrollable. 

Perform an inspection of the fuel spar valve actuator 

position. 

NOTE: The fuel spar valve actuators are located behind main gear doors on the rear spar. 

1. Make sure the L FUEL CONTROL switch on the 

quadrant control stand is in the CUTOFF position. 

NOTE: It is not necessary to cycle the FUEL CONTROL switch to do this inspection. 

2. Inspect the left engine fuel spar valve actuator located in the left rear spar. 

a. Verify the manual override handle on the engine fuel 

spar valve actuator is in the CLOSED position. 

b. Repair or replace any fuel spar valve actuator that is 

not in the CLOSED position (refer to Boeing AMM 

28–22–11). 

3. Make sure the R FUEL CONTROL switch on the 

quadrant control stand is in the CUTOFF position. 

NOTE: It is not necessary to cycle the FUEL CONTROL switch to do this inspection. 

4. Inspect the right engine fuel spar valve actuator located in the right rear spar. 

a. Verify the manual override handle on the engine fuel 

spar valve actuator is in the CLOSED position. 

b. Repair or replace any fuel spar valve actuator that is 

not in the CLOSED position (refer to Boeing AMM 

28–22–11). 

FIGURE 3 TO PARAGRAPH (G) OF THIS AD: AUXILIARY POWER UNIT (APU) FUEL SHUTOFF VALVE POSITION INDICATION

OPERATIONAL CHECK

AWL No. Task Interval Applicability Description 

28–AWL–APU ... ALI 10 DAYS ............................ ALL ..................................... APU Fuel Shutoff Valve Position Indication Operational 

Check. 

INTERVAL NOTE: The 

operational check is not 

required on days when 

the airplane is not used 

in revenue service. The 

operational check must 

be done before further 

flight with an operational 

APU if it has been 10 or 

more calendar days since 

last check.

APPLICABILITY NOTE: Applies to airplanes with an 

actuator installed at the 

APU fuel shutoff valve 

position having part number (P/N) MA20A2027 

(S343T003–56) or 

MA30A1001 (S343T003– 

66).

Concern: The APU fuel shutoff valve actuator design 

can result in airplanes operating with a failed APU 

fuel shutoff valve actuator that is not reported. A latently failed APU fuel shutoff valve actuator could 

prevent fuel shutoff to the APU. In the event of certain APU fires, the potential exists for an APU fire to 

be uncontrollable 

Perform the operational check of the APU fuel shutoff 

valve position indication (unless checked by the 

flightcrew in a manner approved by the principal operations inspector). 

A. Do an operational check of the APU fuel shutoff 

valve position indication. 

1. If the APU is running, unload and shut down the 

APU using standard practices. 

2. Supply electrical power to the airplane using standard practices. 

3. Make sure the APU FIRE switch on the Aft Aisle 

Stand is in the NORMAL (IN) position. 

4. Make sure there is at least 1,000 lbs (500 kgs) of 

fuel in the Left Main Tank. 

5. Move APU Selector switch on the Overhead Panel to 

the ON position and wait approximately 10 seconds 

once the APU selector switch on the overhead panel 

is in the ON position. 

6. Move the APU Selector switch on the Overhead 

Panel to the OFF position. 


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FIGURE 3 TO PARAGRAPH (G) OF THIS AD: AUXILIARY POWER UNIT (APU) FUEL SHUTOFF VALVE POSITION INDICATION

OPERATIONAL CHECK—Continued 

AWL No. Task Interval Applicability Description 

7. Verify the APU FAULT light on the Overhead Panel 

illuminates and then goes off. 

8. If the test fails (light fails to illuminate), before further 

flight requiring APU availability, repair faults as required (refer to Boeing AMM 28–25–02). 

NOTE: Dispatch may be permitted per MMEL 28–25– 

02 if APU is not required for flight. 

(h) No Alternative Actions or Intervals 

After accomplishment of the maintenance 

or inspection program revision 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) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO) 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (j) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) 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. 

(j) Related Information 

For more information about this AD, 

contact Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6509; fax: 425–917–6590; 

email: rebel.nichols@faa.gov. 

(k) Material Incorporated by Reference 

None. 

Issued in Renton, Washington, on October 

16, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26983 Filed 10–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0933; Directorate 

Identifier 2014–NM–098–AD; Amendment 

39–18297; AD 2015–21–05] 

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.27 Mark 

200, 300, 400, 500, 600, and 700 

airplanes. This AD was prompted by a 

design review, which revealed that no 

controlled bonding provisions are 

present on a number of critical locations 

inside the fuel tank or connected to the 

fuel tank wall; and no anti-spray cover 

is installed on the fuel shut-off valve 

(FSOV) in both wings. This AD requires 

installing additional bonding provisions 

in the fuel tank, installing an anti-spray 

cover on the FSOV, and revising the 

airplane maintenance program by 

incorporating fuel airworthiness 

limitation items and critical design 

configuration control limitations. We 

are issuing this AD to prevent an 

ignition source in the fuel tank vapor 

space, which could result in a fuel tank 

explosion and consequent loss of the 

airplane. 

DATES: This AD becomes effective 

November 30, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-0933 or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC. 

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 all Fokker Services B.V. Model 

F.27 Mark 200, 300, 400, 500, 600, and 

700 airplanes. The NPRM published in 

the Federal Register on May 4, 2015 (80 

FR 25247). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0099, dated April 30, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for all Fokker 

Services B.V. Model F.27 Mark 200, 300, 

400, 500, 600, and 700 airplanes. 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 review conducted by Fokker Services 

on the Fokker 27 design in response to these 

regulations revealed that no controlled 

bonding provisions are present on a number 

of critical locations, inside the fuel tank or 

connected to the fuel tank wall, and no antispray cover is installed on the Fueling ShutOff Valve (FSOV) in both wings. 

This condition, if not corrected, could 

create an ignition source in the fuel tank 

vapour space, possibly resulting in a fuel 

tank explosion and consequent loss of the 

aeroplane. 

To address this potential unsafe condition, 

Fokker Services developed a set of bonding 

modifications and anti-spray covers, [and] 

introduced with Service Bulletin (SB) 

SBF27–28–071 Revision 1 (R1), that require 

opening of the fuel tank access panels. More 

information on this subject can be found in 

Fokker Services All Operators Message 

AOF27.043#03. 


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