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# 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


## 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:



### E STIMATED 

### C OSTS

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.


## 65123 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations

F IGURE 

### 1 TO 

### PARAGRAPH 

### (g) OF 

### T HIS 

### AD: E NGINE 

### F UEL 

### S HUTOFF 

### VALVE 

### (F UEL 

### S PAR 

### VALVE 

### ) P OSITION 

### I NDICATION 

### O PERATIONAL 

### C HECK

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 valveposition having part number (P/N) MA20A2027 (S343T003–56) or P/N MA30A1001 (S343T003– 66). Concern: The fuel spar valve actuator design can resultin airplanes operating with a failed fuel spar valve actuator that is not reported. A latently failed fuel sparvalve 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 theflightcrew 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.


## 65124 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations

F IGURE 

### 1 TO 

### PARAGRAPH 

### (g) OF 

### T HIS 

### AD: E NGINE 

### F UEL 

### S HUTOFF 

### VALVE 

### (F UEL 

### S PAR 

### VALVE 

### ) P OSITION 

### I NDICATION 

### O PERATIONAL 

### C HECK

### —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).


## 65125 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations

F IGURE 

### 2 TO 

### PARAGRAPH 

### ( G 

### ) OF 

### T HIS 

### AD: E NGINE 

### F UEL 

### S HUTOFF 

### VALVE 

### (F UEL 

### S PAR 

### VALVE 

### ) ACTUATOR 

### I NSPECTION

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 requiredon 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 valveposition having part number (P/N) MA20A2027 (S343T003–56) or P/N MA30A1001 (S343T003– 66). Concern: The fuel spar valve actuator design can resultin airplanes operating with a failed fuel spar valve actuator that is not reported. A latently failed fuel sparvalve 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).



### F IGURE 

### 3 TO 

### PARAGRAPH 

### ( G 

### ) OF 

### T HIS 

### AD: A UXILIARY 

### P OWER 

### U NIT 

### (APU) F UEL 

### S HUTOFF 

### VALVE 

### P OSITION 

### I NDICATION 

### O PERATIONAL 

### C HECK

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 valveposition 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 APUfuel shutoff valve actuator that is not reported. A latently failed APU fuel shutoff valve actuator couldprevent 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 theflightcrew 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.


## 65126 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations

F IGURE 

### 3 TO 

### PARAGRAPH 

### ( G 

### ) OF 

### T HIS 

### AD: A UXILIARY 

### P OWER 

### U NIT 

### (APU) F UEL 

### S HUTOFF 

### VALVE 

### P OSITION 

### I NDICATION 

### O PERATIONAL 

### C HECK

### —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 orconnected 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.