AD 2015-21-10 ACTIVE

We are superseding Airworthiness Directive (AD) 2015-19-03 for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and - 900ER series airplanes. AD 2015-19-03 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 2015-19-03. We are issuing this AD to detect and correct latent failures of the fuel shutoff valve to the engine, which could result in the inability to shut off fuel to the engine and, in case of certain engine fires, an uncontrollable fire that could lead to wing failure.

Final rule; request for comments.

Adoption of the Amendment \n\n\n\tAccordingly, 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: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n0 1. The authority citation for part 39 continues to read as follows: \n\n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n\n\nSec. 39.13 (Amended) \n\n\n\n0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2015-19-03, Amendment 39-18266 (80 FR 55527, September 16, 2015), and adding the following new AD: \n\n2015-21-10 The Boeing Company: Amendment 39-18303; Docket No. FAA- 2015-4208; Directorate Identifier 2015-NM-152-AD. \n\n(a) Effective Date \n\n\n\tThis AD is effective October 28, 2015. \n\n(b) Affected ADs \n\n\n\tThis AD replaces AD 2015-19-03, Amendment 39-18266 (80 FR 55527, September 16, 2015). \n\n(c) Applicability \n\n\n\tThis AD applies to all The Boeing Company Model 737-600, -700, - 700C, -800, -900, and -900ER seriesairplanes, certificated in any category. \n\n(d) Subject \n\n\n\tAir Transport Association (ATA) of America Code 2823, Fuel Selector/Shutoff Valve. \n\n(e) Unsafe Condition \n\n\n\tThis 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, which could result in the inability to shut off fuel to the engine and, in case of certain engine fires, an uncontrollable fire that could lead to wing failure. \n\n(f) Compliance \n\n\n\tComply with this AD within the compliance times specified, unless already done. \n\n(g) Revision of Maintenance or Inspection Program \n\n\n\tWithin 30 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to add airworthiness limitation number 28-AWL-MOV, ''Engine Fuel Shutoff Valve (Fuel Spar Valve) Position Indication Operational Check,'' by incorporating the information specified in figure 1 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 28-AWL-MOV is within 10 days after accomplishing the maintenance or inspection program revision required by this paragraph. \n\n\n\tFigure 1 to Paragraph (g) of This AD--Engine Fuel Shutoff Valve (Fuel Spar Valve) Position Indication \n\tOperational Check ---------------------------------------------------------------------------------------------------------------- \n\tAWL No. Task Interval Applicability Description ---------------------------------------------------------------------------------------------------------------- 28-AWL-MOV...................... ALI DAILY.............. 737-600, -700, - Engine Fuel Shutoff \n\t700C, -800, -900, Valve (Fuel Spar \n\tand -900ER series Valve) Position \n\tairplanes.Indication Operational \n\tCheck. \n\tINTERVAL NOTE: The APPLICABILITY Concern: The fuel spar \n\toperational check NOTE: Only valve actuator design \n\tis not required on applies to can result in \n\tdays when the airplanes with a airplanes operating \n\tairplane is not fuel spar valve with a failed fuel \n\tused in revenue actuator having spar valve actuator \n\tservice. part number that is not reported. \n\tThe check must be MA20A2027 A latently failed fuel \n\tdone before (S343T003-56) or spar valve actuator \n\tfurther flight MA30A1001 could prevent fuel \n\tonce the airplane (S343T003-66) shutoff to an engine. \n\tis returned to installed at the In the event of \n\trevenue service. engine fuel spar certain engine fires, \n\tvalve positions. the potential exists \n\tfor an engine fire to \n\tbe uncontrollable. \n\tPerform one of the \n\tfollowing checks of \n\tthe engine fuel spar \n\tvalve position (unless \n\tchecked by the \n\tflightcrew in a manner \n\tapproved by the \n\tprincipal operations \n\tinspector): \n\tA. Operational Check \n\tduring engine \n\tshutdown. \n\t1. Do an operational \n\tcheck of the left \n\tengine fuel spar valve \n\tactuator. \n\ta. As the ENG 1 START \n\tLEVER on the CONTROL \n\tSTAND is moved to the \n\tCUTOFF position, \n\tverify the SPAR VALVE \n\tCLOSED indication \n\tlight on the OVERHEAD \n\tPANEL for No.1 Engine \n\tchanges from OFF to \n\tBRIGHT then DIM. \n\tb. If the test fails \n\t(bright light fails to \n\tilluminate), before \n\tfurther flight, repair \n\tfaults as required \n\t(refer to Boeing \n\tAircraft Maintenance \n\tManual (AMM) 28-22- \n\t11). \n\t2. Do an operational \n\tcheck of the right \n\tengine fuel spar valve \n\tactuator. \n\ta. As the ENG 2 START \n\tLEVER on the CONTROL \n\tSTAND is moved to the \n\tCUTOFF position, \n\tverify the SPAR VALVE \n\tCLOSED indication \n\tlight on the OVERHEAD \n\tPANEL for No. 2Engine \n\tchanges from OFF to \n\tBRIGHT then DIM. \n\n((Page 65133)) \n\n\n\n\n\tb. If the test fails \n\t(bright light fails to \n\tilluminate), before \n\tfurther flight, repair \n\tfaults as required \n\t(refer to Boeing AMM \n\t28-22-11). \n\tB. Operational check \n\tduring engine start. \n\t1. Do an operational \n\tcheck of the left \n\tengine fuel spar valve \n\tactuator. \n\ta. As the ENG 1 START \n\tLEVER on the CONTROL \n\tSTAND is moved to the \n\tIDLE position, verify \n\tthe SPAR VALVE CLOSED \n\tindication light on \n\tthe OVERHEAD PANEL for \n\tNo. 1 Engine changes \n\tfrom DIM to BRIGHT \n\tthen OFF. \n\tb. If the test fails \n\t(bright light fails to \n\tilluminate), before \n\tfurther flight, repair \n\tfaults as required \n\t(refer to Boeing AMM \n\t28-22-11). \n\t2. Do an operational \n\tcheck of the right \n\tengine fuel spar valve \n\tactuator. \n\ta. As the ENG 2 START \n\tLEVER on the CONTROL \n\tSTAND is moved to the \n\tIDLE position, verify \n\tthe SPAR VALVE CLOSED \n\tindication light on \n\tthe OVERHEAD PANEL for \n\tNo. 2 Engine changes \n\tfrom DIM to BRIGHT \n\tthen OFF. \n\tb. If the test fails \n\t(bright light fails to \n\tilluminate), before \n\tfurther flight, repair \n\tfaults as required \n\t(refer to Boeing AMM \n\t28-22-11). \n\tC. Operational check \n\twithout engine \n\toperation. \n\t1. Supply electrical \n\tpower to airplane \n\tusing standard \n\tpractices. \n\t2. Make sure No. 1 and \n\tNo. 2 Engine FIRE \n\tswitches on the Aft \n\tElectronic Panel are \n\tin the NORMAL (IN) \n\tposition. \n\t3. Make sure No. 1 and \n\tNo. 2 Engine Start \n\tSwitches on the \n\tForward Overhead Panel \n\tare in the OFF or AUTO \n\tposition. \n\t4. Do an operational \n\tcheck to the left \n\tengine fuel spar valve \n\tactuator. \n\ta. Move ENG 1 START \n\tLEVER on the CONTROL \n\tSTAND to the IDLE \n\tposition and wait \n\tapproximately 10 \n\tseconds. \n\tNOTE: It is normal \n\tunder this test \n\tcondition for the ENG \n\tVALVE CLOSED \n\tindication light on \n\tthe OVERHEAD PANEL to \n\ttransition from DIM to \n\tBRIGHTand stay \n\tBRIGHT. \n\tb. Move ENG 1 START \n\tLEVER on the CONTROL \n\tSTAND to the CUTOFF \n\tposition. \n\tc. Verify the SPAR \n\tVALVE CLOSED \n\tindication light on \n\tthe OVERHEAD PANEL for \n\tNo. 1 Engine changes \n\tfrom OFF to BRIGHT \n\tthen DIM. \n\td. If the test fails \n\t(bright light fails to \n\tilluminate), before \n\tfurther flight, repair \n\tfaults as required \n\t(refer to Boeing AMM \n\t28-22-11). \n\t5. Do an operational \n\tcheck of the right \n\tengine fuel spar valve \n\tactuator. \n\ta. Move ENG 2 START \n\tLEVER on the CONTROL \n\tSTAND to the IDLE \n\tposition and wait \n\tapproximately 10 \n\tseconds. \n\tNOTE: It is normal \n\tunder this test \n\tcondition for the ENG \n\tVALVE CLOSED \n\tindication light on \n\tthe OVERHEAD PANEL to \n\ttransition from DIM to \n\tBRIGHT and stay \n\tBRIGHT. \n\tb. Move ENG 2 START \n\tLEVER on the CONTROL \n\tSTAND to the CUTOFF \n\tposition. \n\tc. Verify the SPAR \n\tVALVE CLOSED \n\tindication light on \n\tthe OVERHEAD PANEL for \n\tNo.2 Engine changes \n\tfromOFF to BRIGHT \n\tthen DIM. \n\td. If the test fails \n\t(bright light fails to \n\tilluminate), before \n\tfurther flight, repair \n\tfaults as required \n\t(refer to Boeing AMM \n\t28-22-11). \n\tD. Perform an \n\tinspection of the \n\tengine fuel spar valve \n\tactuator position. \n\n((Page 65134)) \n\n\n\n\n\tNOTE: This inspection \n\tmay be used whenever \n\tthe SPAR VALVE light \n\tdoes not function \n\tproperly. \n\t1. Make sure the ENG 1 \n\tSTART LEVER on the \n\tCONTROL STAND is in \n\tthe CUTOFF position. \n\tNOTE: It is not \n\tnecessary to cycle the \n\tSTART LEVER to do this \n\tinspection. \n\t2. Inspect the left \n\tengine fuel spar valve \n\tactuator located in \n\tthe left front spar. \n\tNOTE: The left engine \n\tfuel spar valve \n\tactuator is on the \n\tleft wing front spar \n\toutboard of the engine \n\tstrut. Access is \n\tthrough access panel \n\t521BB on the left wing \n\tleading edge. \n\ta. Verify the manual \n\toverride handle on the \n\tengine fuel spar valve \n\tactuator is in the \n\tCLOSED position. \n\tb. Repair or replace \n\tany engine fuel spar \n\tvalve actuator that is \n\tnot in the CLOSED \n\tposition (refer to \n\tBoeing AMM 28-22-11). \n\t3. Make sure the ENG 2 \n\tSTART LEVER on the \n\tCONTROL STAND is in \n\tthe CUTOFF position. \n\tNOTE: It is not \n\tnecessary to cycle the \n\tSTART LEVER to do this \n\tinspection. \n\t4. Inspect the right \n\tengine fuel spar valve \n\tactuator located in \n\tthe right front spar. \n\tNOTE: The right engine \n\tfuel spar valve \n\tactuator is on the \n\tright wing front spar \n\toutboard of the engine \n\tstrut. Access is \n\tthrough access panel \n\t621BB on the right \n\twing leading edge. \n\ta. Verify the manual \n\toverride handle on the \n\tengine fuel spar valve \n\tactuator is in the \n\tCLOSED position. \n\tb. Repair or replace \n\tany engine fuel spar \n\tvalve actuator that is \n\tnot in the CLOSED \n\tposition (refer to \n\tBoeing AMM 28-22-11). ---------------------------------------------------------------------------------------------------------------- \n\n(h) No Alternative Actions or Intervals \n\n\n\tAfter 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. \n\n(i) Alternative Methods of Compliance (AMOCs) \n\n\n\t(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. \n\t(2) Before using anyapproved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. \n\n(j) Related Information \n\n\n\tFor 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. \n\n(k) Material Incorporated by Reference \n\n\n\tNone.

Discussion \n\n\n\tOn September 7, 2015, we issued AD 2015-19-03, Amendment 39-18266 (80 FR 55527, September 16, 2015), for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. AD 2015- 19-03 required revising the maintenance or inspection program to include new airworthiness limitations. AD 2015-19-03 resulted from reports of latently failed fuel shutoff valves discovered during fuel filter replacement. We issued AD 2015-19-03 to detect and correct latent failures of the fuel shutoff valve to the engine, which could result in the inability to shut off fuel to the engine and, in case of certain engine fires, an uncontrollable fire that could lead to wing failure. \n\nActions Since AD 2015-19-03, Amendment 39-18266 (80 FR 55527, September 16, 2015), Was Issued \n\n\n\tSince we issued AD 2015-19-03, Amendment 39-18266 (80 FR 55527, September 16, 2015), we have determined that certain language in the airworthiness limitation was not accurate. In paragraph D. of the ''Description'' column of figure 1 to paragraph (g) of AD 2015-19-03, the ''START LEVER'' is identified as a ''FUEL CONTROL switch'' in four locations. In addition, in two locations in paragraph D. of the ''Description'' column of figure 1 to paragraph (g) of AD 2015-19-03, it specifies that fuel spar valve actuators are located in the ''rear spar,'' but the correct location is the ''front spar.'' Also, in two locations in paragraph D. of the ''Description'' column of figure 1 to paragraph (g) of AD 2015-19-03, the term ''quadrant'' is used to describe the control stand, but the correct terminology is ''CONTROL STAND.'' 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, which could result in the inability to shut off fuel to the engine and, in case of certain engine fires, an uncontrollable fire that could lead to wing failure. \n\nFAA's Determination \n\n\n\tWe 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. \n\nAD Requirements \n\n\n\tThis AD requires revising the maintenance or inspection program to include new airworthiness limitations. \n\nInterim Action \n\n\n\tWe 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. \n\nFAA's Justification and Determination of the Effective Date \n\n\n\tWe are superseding AD 2015-19-03, Amendment 39-18266 (80 FR 55527, September 16, 2015), to correct inaccurate terminology in paragraph D. of the ''Description'' column of figure 1 to paragraph (g) of AD 2015- 19-03. We have made no other changes to the requirements published in AD 2015-19-03. 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. \n\nComments Invited \n\n\n\tThis 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-2015-4208 and Directorate Identifier 2015-NM-152- 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. \n\tWe 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. \n\nCosts of Compliance \n\n\n\tWe estimate that this AD affects 1,244 airplanes of U.S. registry. \n\tWe estimate the following costs to comply with this AD: \n\n\n\tEstimated Costs ---------------------------------------------------------------------------------------------------------------- \n\tCost per Cost on U.S. \n\tAction Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Incorporating Airworthiness Limitation 1 work-hour x $85 per $0 $85 $105,740 \n\thour = $85. ---------------------------------------------------------------------------------------------------------------- \n\nAuthority for This Rulemaking \n\n\n\tTitle 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. \n\tWe 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. \n\nRegulatory Findings \n\n\n\tThis 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. \n\tFor the reasons discussed above, I certify that this AD: \n\t(1) Is not a ''significant regulatory action'' under Executive Order 12866, \n\t(2) Is not a ''significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), \n\n((Page 65132)) \n\n\n\t(3) Will not affect intrastate aviation in Alaska, and \n\t(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. \n\nList of Subjects in 14 CFR Part 39 \n\n\n\tAir transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

We must receive any comments on this AD by December 10, 2015. \n\nADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: \n\tFederal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. \n\tFax: 202-493-2251. \n\tMail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. \n\tHand 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. \n\nExamining the AD Docket \n\n\n\tYou may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 4208; 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.

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: \n\n((Page 65131)) \n\n425-917-6590; email: rebel.nichols@faa.gov.