Airworthiness Directives; The Boeing Company Airplanes, 65121-65126 [2015-26983]

Download as PDF 65121 Rules and Regulations Federal Register Vol. 80, No. 206 Monday, October 26, 2015 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. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Examining the AD Docket 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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: 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. asabaliauskas on DSK5VPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 17:27 Oct 23, 2015 Jkt 238001 • 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. 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. 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 SUPPLEMENTARY INFORMATION: 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. Discussion AD Requirements 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. PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 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 E:\FR\FM\26OCR1.SGM 26OCR1 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 Incorporating Airworthiness Limitation ............ 1 work-hour × $85 per hour = $85 ................. 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. asabaliauskas on DSK5VPTVN1PROD with RULES 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), VerDate Sep<11>2014 17:27 Oct 23, 2015 Jkt 238001 Cost per product Parts cost $0 Cost on U.S. operators $85 (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. (c) Applicability List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. $38,250 Air Transport Association (ATA) of America Code 28, Fuel. 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 Authority: 49 U.S.C. 106(g), 40113, 44701. [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). PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 (d) Subject (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 1. The authority citation for part 39 continues to read as follows: ■ § 39.13 This AD applies to all The Boeing Company Model 767–200, –300, –300F, and –400ER series airplanes, certificated in any category. 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. E:\FR\FM\26OCR1.SGM 26OCR1 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations 65123 FIGURE 1 TO PARAGRAPH (g) OF THIS AD: ENGINE FUEL SHUTOFF VALVE (FUEL SPAR VALVE) POSITION INDICATION OPERATIONAL CHECK AWL No. Task 28–AWL–ENG ... ALI Interval Applicability Description DAILY ................................. 767–200, –300, and –300F airplanes. 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). Engine Fuel Shutoff Valve (Fuel Spar Valve) Position Indication Operational Check. 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 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. VerDate Sep<11>2014 17:27 Oct 23, 2015 Jkt 238001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\26OCR1.SGM 26OCR1 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 asabaliauskas on DSK5VPTVN1PROD with RULES 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). VerDate Sep<11>2014 17:27 Oct 23, 2015 Jkt 238001 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\26OCR1.SGM 26OCR1 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations 65125 FIGURE 2 TO PARAGRAPH (G) OF THIS AD: ENGINE FUEL SHUTOFF VALVE (FUEL SPAR VALVE) ACTUATOR INSPECTION AWL No. Task 28-AWL-MOV .... ALI Interval Applicability Description 10 DAYS ............................ 767–400ER series airplanes. 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). Engine Fuel Shutoff Valve (Fuel Spar Valve) Actuator Inspection. 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). 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. FIGURE 3 TO PARAGRAPH (G) OF THIS AD: AUXILIARY POWER UNIT (APU) FUEL SHUTOFF VALVE POSITION INDICATION OPERATIONAL CHECK AWL No. Task asabaliauskas on DSK5VPTVN1PROD with RULES VerDate Sep<11>2014 ALI Applicability Description 10 DAYS ............................ ALL ..................................... 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. 28–AWL–APU ... Interval 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). APU Fuel Shutoff Valve Position Indication Operational Check. 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. 17:27 Oct 23, 2015 Jkt 238001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\26OCR1.SGM 26OCR1 65126 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations 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 DEPARTMENT OF TRANSPORTATION 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. 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 (i) Alternative Methods of Compliance (AMOCs) Airworthiness Directives; Fokker Services B.V. Airplanes (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. AGENCY: (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 asabaliauskas on DSK5VPTVN1PROD with RULES 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 VerDate Sep<11>2014 17:27 Oct 23, 2015 Jkt 238001 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. 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. SUMMARY: 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. DATES: PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 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: FOR FURTHER INFORMATION CONTACT: 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. E:\FR\FM\26OCR1.SGM 26OCR1

Agencies

[Federal Register Volume 80, Number 206 (Monday, October 26, 2015)]
[Rules and Regulations]
[Pages 65121-65126]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-26983]



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

[[Page 65121]]



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

[[Page 65122]]

``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
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Incorporating Airworthiness Limitation  1 work-hour x $85 per                 $0             $85         $38,250
                                         hour = $85.
----------------------------------------------------------------------------------------------------------------

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

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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.

[[Page 65123]]



      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 -  Engine Fuel Shutoff Valve
                                                                  300F airplanes.       (Fuel Spar Valve)
                                                                                        Position Indication
                                                                                        Operational Check.
                                           INTERVAL NOTE: The    APPLICABILITY NOTE:   Concern: The fuel spar
                                            operational check     Applies to            valve actuator design
                                            is not required on    airplanes with an     can result in airplanes
                                            days when the         actuator installed    operating with a failed
                                            airplane is not       at the engine fuel    fuel spar valve actuator
                                            used in revenue       spar valve position   that is not reported. A
                                            service.              having part number    latently failed fuel
                                           The check must be      (P/N) MA20A2027       spar valve actuator
                                            done before further   (S343T003-56) or P/   could prevent fuel
                                            flight once the       N MA30A1001           shutoff to an engine. In
                                            airplane is           (S343T003-66).        the event of certain
                                            returned to revenue                         engine fires, the
                                            service.                                    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.

[[Page 65124]]

 
                                                                                       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).
----------------------------------------------------------------------------------------------------------------


[[Page 65125]]


      Figure 2 to Paragraph (g) of This AD: Engine Fuel Shutoff Valve (Fuel Spar Valve) Actuator Inspection
----------------------------------------------------------------------------------------------------------------
          AWL No.                Task            Interval            Applicability            Description
----------------------------------------------------------------------------------------------------------------
28[dash]AWL[dash]MOV......  ALI            10 DAYS.............  767-400ER series      Engine Fuel Shutoff Valve
                                                                  airplanes.            (Fuel Spar Valve)
                                                                                        Actuator Inspection.
                                           INTERVAL NOTE: The    APPLICABILITY NOTE:   Concern: The fuel spar
                                            inspection is not     Applies to            valve actuator design
                                            required on days      airplanes with an     can result in airplanes
                                            when the airplane     actuator installed    operating with a failed
                                            is not used in        at the engine fuel    fuel spar valve actuator
                                            revenue service.      spar valve position   that is not reported. A
                                           The inspection must    having part number    latently failed fuel
                                            be done before        (P/N) MA20A2027       spar valve actuator
                                            further flight if     (S343T003-56) or P/   would prevent fuel
                                            it has been 10 or     N MA30A1001           shutoff to an engine. In
                                            more calendar days    (S343T003-66).        the event of certain
                                            since last                                  engine fires, the
                                            inspection.                                 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    APPLICABILITY NOTE:   Concern: The APU fuel
                                            operational check     Applies to            shutoff valve actuator
                                            is not required on    airplanes with an     design can result in
                                            days when the         actuator installed    airplanes operating with
                                            airplane is not       at the APU fuel       a failed APU fuel
                                            used in revenue       shutoff valve         shutoff valve actuator
                                            service. The          position having       that is not reported. A
                                            operational check     part number (P/N)     latently failed APU fuel
                                            must be done before   MA20A2027 (S343T003-  shutoff valve actuator
                                            further flight with   56) or MA30A1001      could prevent fuel
                                            an operational APU    (S343T003-66).        shutoff to the APU. In
                                            if it has been 10                           the event of certain APU
                                            or more calendar                            fires, the potential
                                            days since last                             exists for an APU fire
                                            check.                                      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.

[[Page 65126]]

 
                                                                                       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-AMOC-Requests@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