Airworthiness Directives; The Boeing Company Airplanes, 65130-65134 [2015-26992]

Download as PDF 65130 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations Alert Service Bulletin No. 76–67–57, Basic Issue, dated September 10, 2015, illustrate slippage marks across a pushrod tube and jamnut. the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2015–19–51 Sikorsky Aircraft Corporation: Amendment 39–18300; Docket No. FAA–2015–3940; Directorate Identifier 2015–SW–065–AD. (a) Applicability This AD applies to Model S–76A, S–76B, S–76C, and S–76D helicopters with main rotor (M/R) servo input control pushrod (pushrod) assembly part number (P/N) 76400–00034–059 or tail rotor (T/R) pushrod assembly P/N 76400–00014–071 installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a loose jamnut. This condition could result in failure of a pushrod assembly, loss of M/R or T/R flight control, and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective November 10, 2015 to all persons except those persons to whom it was made immediately effective by Emergency AD 2015–19–51, issued on September 14, 2015, which contains the requirements of this AD. asabaliauskas on DSK5VPTVN1PROD with RULES (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions Within five hours time-in-service: (1) Inspect each pushrod end to determine whether a 0.020 inch diameter lockwire can pass through the inspection hole. (i) If the lockwire passes through the inspection hole, replace the pushrod assembly. (ii) If the lockwire does not pass through the inspection hole, inspect the jamnut to determine whether it is seated against the pushrod and whether it can be turned with finger pressure. If the jamnut is not seated against the pushrod or can be turned with finger pressure, replace the pushrod assembly. (2) Apply two slippage marks across each pushrod tube and jamnut as follows: (i) Clean the area where a slippage mark is to be applied. (ii) Apply two slippage marks across the pushrod tube and jamnut, parallel and on opposite sides of each other. Each slippage mark must extend at least 0.5 inch onto the pushrod tube and must not cover the inspection hole. Figures 2 and 4 of Sikorsky VerDate Sep<11>2014 17:27 Oct 23, 2015 Jkt 238001 (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Blaine Williams, Aerospace Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238–7161; email blaine.williams@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (g) Additional Information Sikorsky Alert Service Bulletin No. 76–67– 57, Basic Issue, dated September 10, 2015, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry Road, Trumbull, CT 06611; telephone 1–800–Winged–S or 203– 416–4299; email sikorskywcs@sikorsky.com. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. (h) Subject Joint Aircraft Service Component (JASC) Code: 2700, Flight Control System. Issued in Fort Worth, Texas, on October 9, 2015. Lance T. Gant, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2015–26949 Filed 10–23–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–4208; Directorate Identifier 2015–NM–152–AD; Amendment 39–18303; AD 2015–21–10] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 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. 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. SUMMARY: 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– 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. 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: E:\FR\FM\26OCR1.SGM 26OCR1 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations 425–917–6590; email: rebel.nichols@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion On 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. Actions Since AD 2015–19–03, Amendment 39–18266 (80 FR 55527, September 16, 2015), Was Issued Since 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. 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 2015–19–03, Amendment 39–18266 (80 FR 55527, September 16, 2015), to correct inaccurate terminology in paragraph D. of the ‘‘Description’’ column of figure 1 65131 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. 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–2015–4208 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. 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 1,244 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 ................. asabaliauskas on DSK5VPTVN1PROD with RULES 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 VerDate Sep<11>2014 17:27 Oct 23, 2015 Jkt 238001 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 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 Cost per product Parts cost $0 $85 Cost on U.S. operators $105,740 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), E:\FR\FM\26OCR1.SGM 26OCR1 65132 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations (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 2015–21–10 The Boeing Company: Amendment 39–18303; Docket No. FAA–2015–4208; Directorate Identifier 2015–NM–152–AD. (a) Effective Date This AD is effective October 28, 2015. (b) Affected ADs This AD replaces AD 2015–19–03, Amendment 39–18266 (80 FR 55527, September 16, 2015). (c) Applicability This AD applies to all The Boeing Company Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 2823, Fuel Selector/Shutoff Valve. 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 2015–19–03, Amendment 39–18266 (80 FR 55527, September 16, 2015), and adding the following new AD: [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) ■ (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, 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. (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 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. FIGURE 1 TO PARAGRAPH (g) OF THIS AD—ENGINE FUEL SHUTOFF VALVE (FUEL SPAR VALVE) POSITION INDICATION OPERATIONAL CHECK AWL No. 28–AWL–MOV ........................ Task ALI Interval Applicability Description DAILY ............................ 737–600, –700, –700C, –800, –900, and –900ER series airplanes. APPLICABILITY NOTE: Only applies to airplanes with a fuel spar valve actuator having part number MA20A2027 (S343T003–56) or MA30A1001 (S343T003–66) installed at the engine fuel spar valve positions. Engine Fuel Shutoff Valve (Fuel Spar Valve) Position Indication Operational Check. 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 00012 Fmt 4700 Sfmt 4700 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 of the engine 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 ENG 1 START LEVER on the CONTROL STAND is moved to the CUTOFF position, verify the SPAR VALVE CLOSED indication light on the OVERHEAD PANEL for No.1 Engine changes from OFF to BRIGHT then DIM. b. If the test fails (bright light fails to illuminate), before further flight, repair faults as required (refer to Boeing Aircraft Maintenance Manual (AMM) 28–22–11). 2. Do an operational check of the right engine fuel spar valve actuator. a. As the ENG 2 START LEVER on the CONTROL STAND is moved to the CUTOFF position, verify the SPAR VALVE CLOSED indication light on the OVERHEAD PANEL for No. 2 Engine changes from OFF to BRIGHT then DIM. E:\FR\FM\26OCR1.SGM 26OCR1 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations 65133 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 b. If the test fails (bright 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 ENG 1 START LEVER on the CONTROL STAND is moved to the IDLE position, verify the SPAR VALVE CLOSED indication light on the OVERHEAD PANEL for No. 1 Engine changes from DIM to BRIGHT then OFF. b. If the test fails (bright 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 ENG 2 START LEVER on the CONTROL STAND is moved to the IDLE position, verify the SPAR VALVE CLOSED indication light on the OVERHEAD PANEL for No. 2 Engine changes from DIM to BRIGHT then OFF. b. If the test fails (bright 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 airplane using standard practices. 2. Make sure No. 1 and No. 2 Engine FIRE switches on the Aft Electronic Panel are in the NORMAL (IN) position. 3. Make sure No. 1 and No. 2 Engine Start Switches on the Forward Overhead Panel are in the OFF or AUTO position. 4. Do an operational check to the left engine fuel spar valve actuator. a. Move ENG 1 START LEVER on the CONTROL STAND to the IDLE position and wait approximately 10 seconds. NOTE: It is normal under this test condition for the ENG VALVE CLOSED indication light on the OVERHEAD PANEL to transition from DIM to BRIGHT and stay BRIGHT. b. Move ENG 1 START LEVER on the CONTROL STAND to the CUTOFF position. c. Verify the SPAR VALVE CLOSED indication light on the OVERHEAD PANEL for No. 1 Engine changes from OFF to BRIGHT then DIM. d. If the test fails (bright light fails to illuminate), before further flight, repair faults as required (refer to Boeing AMM 28–22–11). 5. Do an operational check of the right engine fuel spar valve actuator. a. Move ENG 2 START LEVER on the CONTROL STAND to the IDLE position and wait approximately 10 seconds. NOTE: It is normal under this test condition for the ENG VALVE CLOSED indication light on the OVERHEAD PANEL to transition from DIM to BRIGHT and stay BRIGHT. b. Move ENG 2 START LEVER on the CONTROL STAND to the CUTOFF position. c. Verify the SPAR VALVE CLOSED indication light on the OVERHEAD PANEL for No.2 Engine changes from OFF to BRIGHT then DIM. d. If the test fails (bright light fails to illuminate), before further flight, repair faults as required (refer to Boeing AMM 28–22–11). D. Perform an inspection of the engine fuel spar valve actuator position. VerDate Sep<11>2014 17:27 Oct 23, 2015 Jkt 238001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\26OCR1.SGM 26OCR1 65134 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations FIGURE 1 TO PARAGRAPH (g) OF THIS AD—ENGINE FUEL SHUTOFF VALVE (FUEL SPAR VALVE) POSITION INDICATION OPERATIONAL CHECK—Continued AWL No. Task Interval Applicability Description NOTE: This inspection may be used whenever the SPAR VALVE light does not function properly. 1. Make sure the ENG 1 START LEVER on the CONTROL STAND is in the CUTOFF position. NOTE: It is not necessary to cycle the START LEVER to do this inspection. 2. Inspect the left engine fuel spar valve actuator located in the left front spar. NOTE: The left engine fuel spar valve actuator is on the left wing front spar outboard of the engine strut. Access is through access panel 521BB on the left wing leading edge. a. Verify the manual override handle on the engine fuel spar valve actuator is in the CLOSED position. b. Repair or replace any engine fuel spar valve actuator that is not in the CLOSED position (refer to Boeing AMM 28–22–11). 3. Make sure the ENG 2 START LEVER on the CONTROL STAND is in the CUTOFF position. NOTE: It is not necessary to cycle the START LEVER to do this inspection. 4. Inspect the right engine fuel spar valve actuator located in the right front spar. NOTE: The right engine fuel spar valve actuator is on the right wing front spar outboard of the engine strut. Access is through access panel 621BB on the right wing leading edge. a. Verify the manual override handle on the engine fuel spar valve actuator is in the CLOSED position. b. Repair or replace any engine fuel spar valve actuator that is not in the CLOSED position (refer to Boeing AMM 28–22–11). (h) No Alternative Actions or Intervals (j) Related Information 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. 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. None. asabaliauskas on DSK5VPTVN1PROD with RULES (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (j) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. VerDate Sep<11>2014 17:27 Oct 23, 2015 Jkt 238001 (k) Material Incorporated by Reference Issued in Renton, Washington, on October 16, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–26992 Filed 10–23–15; 8:45 am] BILLING CODE 4910–13–P PO 00000 DEPARTMENT OF HOMELAND SECURITY U.S. Customs and Border Protection DEPARTMENT OF THE TREASURY 19 CFR Parts 4, 7, 10, 12, 18, 19, 24, 54, 102, 113, 123, 125, 128, 132, 134, 141, 142, 143, 144, 145, 146, 148, 151, 152, 158, 163, 174, 181, and 191 [CBP Dec. No. 15–14; USCBP–2015–0045] RIN 1515–AE03 Automated Commercial Environment (ACE) Filings for Electronic Entry/Entry Summary (Cargo Release and Related Entry); Correction U.S. Customs and Border Protection, Department of Homeland Security; Department of the Treasury. ACTION: Interim final rule; correction. AGENCY: U.S. Customs and Border Protection (CBP) published an Interim Final Rule (CBP Dec. 15–14) on October 13, 2015, in the Federal Register, which amends the CBP regulations to reflect SUMMARY: Frm 00014 Fmt 4700 Sfmt 4700 E:\FR\FM\26OCR1.SGM 26OCR1

Agencies

[Federal Register Volume 80, Number 206 (Monday, October 26, 2015)]
[Rules and Regulations]
[Pages 65130-65134]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-26992]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4208; Directorate Identifier 2015-NM-152-AD; 
Amendment 39-18303; AD 2015-21-10]
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) 2015-19-03 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.

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-
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.

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:

[[Page 65131]]

425-917-6590; email: rebel.nichols@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    On 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.

Actions Since AD 2015-19-03, Amendment 39-18266 (80 FR 55527, September 
16, 2015), Was Issued

    Since 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.

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 2015-19-03, 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.

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-2015-4208 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.
    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 1,244 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        $105,740
                                         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),

[[Page 65132]]

    (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) 
2015-19-03, Amendment 39-18266 (80 FR 55527, September 16, 2015), and 
adding the following new AD:

2015-21-10 The Boeing Company: Amendment 39-18303; Docket No. FAA-
2015-4208; Directorate Identifier 2015-NM-152-AD.

(a) Effective Date

    This AD is effective October 28, 2015.

(b) Affected ADs

    This AD replaces AD 2015-19-03, Amendment 39-18266 (80 FR 55527, 
September 16, 2015).

(c) Applicability

    This AD applies to all The Boeing Company Model 737-600, -700, -
700C, -800, -900, and -900ER series airplanes, certificated in any 
category.

(d) Subject

    Air Transport Association (ATA) of America Code 2823, Fuel 
Selector/Shutoff Valve.

(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, 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.

(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 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.

      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-MOV......................  ALI           DAILY..............  737-600, -700, -    Engine Fuel Shutoff
                                                                      700C, -800, -900,   Valve (Fuel Spar
                                                                      and -900ER series   Valve) Position
                                                                      airplanes.          Indication Operational
                                                                                          Check.
                                                INTERVAL NOTE: The   APPLICABILITY       Concern: The fuel spar
                                                 operational check    NOTE: Only          valve actuator design
                                                 is not required on   applies to          can result in
                                                 days when the        airplanes with a    airplanes operating
                                                 airplane is not      fuel spar valve     with a failed fuel
                                                 used in revenue      actuator having     spar valve actuator
                                                 service.             part number         that is not reported.
                                                The check must be     MA20A2027           A latently failed fuel
                                                 done before          (S343T003-56) or    spar valve actuator
                                                 further flight       MA30A1001           could prevent fuel
                                                 once the airplane    (S343T003-66)       shutoff to an engine.
                                                 is returned to       installed at the    In the event of
                                                 revenue service.     engine fuel spar    certain engine fires,
                                                                      valve positions.    the potential exists
                                                                                          for an engine fire to
                                                                                          be uncontrollable.
                                                                                         Perform one of the
                                                                                          following checks of
                                                                                          the engine 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 ENG 1 START
                                                                                          LEVER on the CONTROL
                                                                                          STAND is moved to the
                                                                                          CUTOFF position,
                                                                                          verify the SPAR VALVE
                                                                                          CLOSED indication
                                                                                          light on the OVERHEAD
                                                                                          PANEL for No.1 Engine
                                                                                          changes from OFF to
                                                                                          BRIGHT then DIM.
                                                                                         b. If the test fails
                                                                                          (bright light fails to
                                                                                          illuminate), before
                                                                                          further flight, repair
                                                                                          faults as required
                                                                                          (refer to Boeing
                                                                                          Aircraft Maintenance
                                                                                          Manual (AMM) 28-22-
                                                                                          11).
                                                                                         2. Do an operational
                                                                                          check of the right
                                                                                          engine fuel spar valve
                                                                                          actuator.
                                                                                         a. As the ENG 2 START
                                                                                          LEVER on the CONTROL
                                                                                          STAND is moved to the
                                                                                          CUTOFF position,
                                                                                          verify the SPAR VALVE
                                                                                          CLOSED indication
                                                                                          light on the OVERHEAD
                                                                                          PANEL for No. 2 Engine
                                                                                          changes from OFF to
                                                                                          BRIGHT then DIM.

[[Page 65133]]

 
                                                                                         b. If the test fails
                                                                                          (bright 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 ENG 1 START
                                                                                          LEVER on the CONTROL
                                                                                          STAND is moved to the
                                                                                          IDLE position, verify
                                                                                          the SPAR VALVE CLOSED
                                                                                          indication light on
                                                                                          the OVERHEAD PANEL for
                                                                                          No. 1 Engine changes
                                                                                          from DIM to BRIGHT
                                                                                          then OFF.
                                                                                         b. If the test fails
                                                                                          (bright 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 ENG 2 START
                                                                                          LEVER on the CONTROL
                                                                                          STAND is moved to the
                                                                                          IDLE position, verify
                                                                                          the SPAR VALVE CLOSED
                                                                                          indication light on
                                                                                          the OVERHEAD PANEL for
                                                                                          No. 2 Engine changes
                                                                                          from DIM to BRIGHT
                                                                                          then OFF.
                                                                                         b. If the test fails
                                                                                          (bright 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 airplane
                                                                                          using standard
                                                                                          practices.
                                                                                         2. Make sure No. 1 and
                                                                                          No. 2 Engine FIRE
                                                                                          switches on the Aft
                                                                                          Electronic Panel are
                                                                                          in the NORMAL (IN)
                                                                                          position.
                                                                                         3. Make sure No. 1 and
                                                                                          No. 2 Engine Start
                                                                                          Switches on the
                                                                                          Forward Overhead Panel
                                                                                          are in the OFF or AUTO
                                                                                          position.
                                                                                         4. Do an operational
                                                                                          check to the left
                                                                                          engine fuel spar valve
                                                                                          actuator.
                                                                                         a. Move ENG 1 START
                                                                                          LEVER on the CONTROL
                                                                                          STAND to the IDLE
                                                                                          position and wait
                                                                                          approximately 10
                                                                                          seconds.
                                                                                         NOTE: It is normal
                                                                                          under this test
                                                                                          condition for the ENG
                                                                                          VALVE CLOSED
                                                                                          indication light on
                                                                                          the OVERHEAD PANEL to
                                                                                          transition from DIM to
                                                                                          BRIGHT and stay
                                                                                          BRIGHT.
                                                                                         b. Move ENG 1 START
                                                                                          LEVER on the CONTROL
                                                                                          STAND to the CUTOFF
                                                                                          position.
                                                                                         c. Verify the SPAR
                                                                                          VALVE CLOSED
                                                                                          indication light on
                                                                                          the OVERHEAD PANEL for
                                                                                          No. 1 Engine changes
                                                                                          from OFF to BRIGHT
                                                                                          then DIM.
                                                                                         d. If the test fails
                                                                                          (bright light fails to
                                                                                          illuminate), before
                                                                                          further flight, repair
                                                                                          faults as required
                                                                                          (refer to Boeing AMM
                                                                                          28-22-11).
                                                                                         5. Do an operational
                                                                                          check of the right
                                                                                          engine fuel spar valve
                                                                                          actuator.
                                                                                         a. Move ENG 2 START
                                                                                          LEVER on the CONTROL
                                                                                          STAND to the IDLE
                                                                                          position and wait
                                                                                          approximately 10
                                                                                          seconds.
                                                                                         NOTE: It is normal
                                                                                          under this test
                                                                                          condition for the ENG
                                                                                          VALVE CLOSED
                                                                                          indication light on
                                                                                          the OVERHEAD PANEL to
                                                                                          transition from DIM to
                                                                                          BRIGHT and stay
                                                                                          BRIGHT.
                                                                                         b. Move ENG 2 START
                                                                                          LEVER on the CONTROL
                                                                                          STAND to the CUTOFF
                                                                                          position.
                                                                                         c. Verify the SPAR
                                                                                          VALVE CLOSED
                                                                                          indication light on
                                                                                          the OVERHEAD PANEL for
                                                                                          No.2 Engine changes
                                                                                          from OFF to BRIGHT
                                                                                          then DIM.
                                                                                         d. If the test fails
                                                                                          (bright light fails to
                                                                                          illuminate), before
                                                                                          further flight, repair
                                                                                          faults as required
                                                                                          (refer to Boeing AMM
                                                                                          28-22-11).
                                                                                         D. Perform an
                                                                                          inspection of the
                                                                                          engine fuel spar valve
                                                                                          actuator position.

[[Page 65134]]

 
                                                                                         NOTE: This inspection
                                                                                          may be used whenever
                                                                                          the SPAR VALVE light
                                                                                          does not function
                                                                                          properly.
                                                                                         1. Make sure the ENG 1
                                                                                          START LEVER on the
                                                                                          CONTROL STAND is in
                                                                                          the CUTOFF position.
                                                                                         NOTE: It is not
                                                                                          necessary to cycle the
                                                                                          START LEVER to do this
                                                                                          inspection.
                                                                                         2. Inspect the left
                                                                                          engine fuel spar valve
                                                                                          actuator located in
                                                                                          the left front spar.
                                                                                         NOTE: The left engine
                                                                                          fuel spar valve
                                                                                          actuator is on the
                                                                                          left wing front spar
                                                                                          outboard of the engine
                                                                                          strut. Access is
                                                                                          through access panel
                                                                                          521BB on the left wing
                                                                                          leading edge.
                                                                                         a. Verify the manual
                                                                                          override handle on the
                                                                                          engine fuel spar valve
                                                                                          actuator is in the
                                                                                          CLOSED position.
                                                                                         b. Repair or replace
                                                                                          any engine fuel spar
                                                                                          valve actuator that is
                                                                                          not in the CLOSED
                                                                                          position (refer to
                                                                                          Boeing AMM 28-22-11).
                                                                                         3. Make sure the ENG 2
                                                                                          START LEVER on the
                                                                                          CONTROL STAND is in
                                                                                          the CUTOFF position.
                                                                                         NOTE: It is not
                                                                                          necessary to cycle the
                                                                                          START LEVER to do this
                                                                                          inspection.
                                                                                         4. Inspect the right
                                                                                          engine fuel spar valve
                                                                                          actuator located in
                                                                                          the right front spar.
                                                                                         NOTE: The right engine
                                                                                          fuel spar valve
                                                                                          actuator is on the
                                                                                          right wing front spar
                                                                                          outboard of the engine
                                                                                          strut. Access is
                                                                                          through access panel
                                                                                          621BB on the right
                                                                                          wing leading edge.
                                                                                         a. Verify the manual
                                                                                          override handle on the
                                                                                          engine fuel spar valve
                                                                                          actuator is in the
                                                                                          CLOSED position.
                                                                                         b. Repair or replace
                                                                                          any engine fuel spar
                                                                                          valve actuator that is
                                                                                          not in the CLOSED
                                                                                          position (refer to
                                                                                          Boeing AMM 28-22-11).
----------------------------------------------------------------------------------------------------------------

(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. 2015-26992 Filed 10-23-15; 8:45 am]
 BILLING CODE 4910-13-P