80 FR 65130 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 206 (October 26, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 206 (October 26, 2015)
| Page Range | 65130-65134 | |
| FR Document | 2015-26992 |
[Federal Register Volume 80, Number 206 (Monday, October 26, 2015)] [Rules and Regulations] [Pages 65130-65134] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-26992] ----------------------------------------------------------------------- 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
![65130 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations
the FAA amends 14 CFR part 39 as Alert Service Bulletin No. 76–67–57, Basic SUMMARY: We are superseding
follows: Issue, dated September 10, 2015, illustrate Airworthiness Directive (AD) 2015–19–
slippage marks across a pushrod tube and 03 for all The Boeing Company Model
PART 39—AIRWORTHINESS jamnut.
737–600, –700, –700C, –800, –900, and
DIRECTIVES (f) Alternative Methods of Compliance –900ER series airplanes. AD 2015–19–
(AMOCs) 03 required revising the maintenance or
■ 1. The authority citation for part 39
(1) The Manager, Boston Aircraft inspection program to include new
continues to read as follows:
Certification Office, FAA, may approve airworthiness limitations. This AD
Authority: 49 U.S.C. 106(g), 40113, 44701. AMOCs for this AD. Send your proposal to: continues to require a maintenance or
Blaine Williams, Aerospace Engineer, Boston inspection program revision, but with
§ 39.13 [Amended] Aircraft Certification Office, Engine & revised language. This AD was
■ 2. The FAA amends § 39.13 by adding Propeller Directorate, 12 New England
prompted by a determination that
the following new airworthiness Executive Park, Burlington, Massachusetts
01803; telephone (781) 238–7161; email certain language in the airworthiness
directive (AD): limitation was not accurate in AD 2015–
blaine.williams@faa.gov.
2015–19–51 Sikorsky Aircraft (2) For operations conducted under a 14 19–03. We are issuing this AD to detect
Corporation: Amendment 39–18300; Docket CFR part 119 operating certificate or under and correct latent failures of the fuel
No. FAA–2015–3940; Directorate Identifier 14 CFR part 91, subpart K, we suggest that shutoff valve to the engine, which could
2015–SW–065–AD. you notify your principal inspector, or result in the inability to shut off fuel to
(a) Applicability lacking a principal inspector, the manager of the engine and, in case of certain engine
the local flight standards district office or fires, an uncontrollable fire that could
This AD applies to Model S–76A, S–76B, certificate holding district office, before
S–76C, and S–76D helicopters with main lead to wing failure.
operating any aircraft complying with this
rotor (M/R) servo input control pushrod AD through an AMOC. DATES: This AD is effective October 28,
(pushrod) assembly part number (P/N) 2015.
76400–00034–059 or tail rotor (T/R) pushrod (g) Additional Information We must receive any comments on
assembly P/N 76400–00014–071 installed, Sikorsky Alert Service Bulletin No. 76–67– this AD by December 10, 2015.
certificated in any category. 57, Basic Issue, dated September 10, 2015, ADDRESSES: You may send comments,
(b) Unsafe Condition which is not incorporated by reference,
contains additional information about the
using the procedures found in 14 CFR
This AD defines the unsafe condition as a 11.43 and 11.45, by any of the following
subject of this AD. For service information
loose jamnut. This condition could result in methods:
identified in this AD, contact Sikorsky
failure of a pushrod assembly, loss of M/R or
Aircraft Corporation, Customer Service • Federal eRulemaking Portal: Go to
T/R flight control, and subsequent loss of
Engineering, 124 Quarry Road, Trumbull, CT http://www.regulations.gov. Follow the
control of the helicopter.
06611; telephone 1–800–Winged–S or 203– instructions for submitting comments.
(c) Effective Date 416–4299; email sikorskywcs@sikorsky.com. • Fax: 202–493–2251.
This AD becomes effective November 10, You may review a copy of the service • Mail: U.S. Department of
2015 to all persons except those persons to information at the FAA, Office of the Transportation, Docket Operations,
whom it was made immediately effective by Regional Counsel, Southwest Region, 10101
M–30, West Building Ground Floor,
Emergency AD 2015–19–51, issued on Hillwood Pkwy, Room 6N–321, Fort Worth,
TX 76177. Room W12–140, 1200 New Jersey
September 14, 2015, which contains the Avenue SE., Washington, DC 20590.
requirements of this AD. (h) Subject • Hand Delivery: U.S. Department of
(d) Compliance Joint Aircraft Service Component (JASC) Transportation, Docket Operations,
You are responsible for performing each Code: 2700, Flight Control System. M–30, West Building Ground Floor,
action required by this AD within the Issued in Fort Worth, Texas, on October 9, Room W12–140, 1200 New Jersey
specified compliance time unless it has 2015. Avenue SE., Washington, DC 20590,
already been accomplished prior to that time. Lance T. Gant, between 9 a.m. and 5 p.m., Monday
(e) Required Actions Manager, Rotorcraft Directorate, Aircraft through Friday, except Federal holidays.
Within five hours time-in-service: Certification Service. Examining the AD Docket
(1) Inspect each pushrod end to determine [FR Doc. 2015–26949 Filed 10–23–15; 8:45 am]
whether a 0.020 inch diameter lockwire can You may examine the AD docket on
BILLING CODE 4910–13–P
pass through the inspection hole. the Internet at http://
(i) If the lockwire passes through the www.regulations.gov by searching for
inspection hole, replace the pushrod DEPARTMENT OF TRANSPORTATION and locating Docket No. FAA–2015–
assembly. 4208; or in person at the Docket
(ii) If the lockwire does not pass through Federal Aviation Administration Management Facility between 9 a.m.
the inspection hole, inspect the jamnut to and 5 p.m., Monday through Friday,
determine whether it is seated against the except Federal holidays. The AD docket
pushrod and whether it can be turned with 14 CFR Part 39
contains this AD, the regulatory
finger pressure. If the jamnut is not seated [Docket No. FAA–2015–4208; Directorate
against the pushrod or can be turned with evaluation, any comments received, and
Identifier 2015–NM–152–AD; Amendment other information. The street address for
finger pressure, replace the pushrod 39–18303; AD 2015–21–10]
assembly. the Docket Office (phone: 800–647–
(2) Apply two slippage marks across each RIN 2120–AA64 5527) is in the ADDRESSES section.
asabaliauskas on DSK5VPTVN1PROD with RULES
pushrod tube and jamnut as follows: Comments will be available in the AD
(i) Clean the area where a slippage mark is Airworthiness Directives; The Boeing docket shortly after receipt.
to be applied. Company Airplanes FOR FURTHER INFORMATION CONTACT:
(ii) Apply two slippage marks across the
pushrod tube and jamnut, parallel and on AGENCY: Federal Aviation Rebel Nichols, Aerospace Engineer,
opposite sides of each other. Each slippage Administration (FAA), DOT. Propulsion Branch, ANM–140S, FAA,
mark must extend at least 0.5 inch onto the Seattle Aircraft Certification Office,
ACTION: Final rule; request for
pushrod tube and must not cover the 1601 Lind Avenue SW., Renton, WA
comments.
inspection hole. Figures 2 and 4 of Sikorsky 98057–3356; phone: 425–917–6509; fax:
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(3) Will not affect intrastate aviation 2015–19–03, Amendment 39–18266 (80 of the fuel shutoff valve to the engine, which
in Alaska, and FR 55527, September 16, 2015), and could result in the inability to shut off fuel
(4) Will not have a significant adding the following new AD: to the engine and, in case of certain engine
economic impact, positive or negative, 2015–21–10 The Boeing Company:
fires, an uncontrollable fire that could lead to
on a substantial number of small entities wing failure.
Amendment 39–18303; Docket No.
under the criteria of the Regulatory FAA–2015–4208; Directorate Identifier (f) Compliance
Flexibility Act. 2015–NM–152–AD.
Comply with this AD within the
List of Subjects in 14 CFR Part 39 (a) Effective Date compliance times specified, unless already
Air transportation, Aircraft, Aviation This AD is effective October 28, 2015. done.
safety, Incorporation by reference, (g) Revision of Maintenance or Inspection
(b) Affected ADs
Safety. Program
This AD replaces AD 2015–19–03,
Adoption of the Amendment Amendment 39–18266 (80 FR 55527, Within 30 days after the effective date of
Accordingly, under the authority September 16, 2015). this AD, revise the maintenance or inspection
delegated to me by the Administrator, program, as applicable, to add airworthiness
(c) Applicability
the FAA amends part 39 of the Federal limitation number 28–AWL–MOV, ‘‘Engine
This AD applies to all The Boeing Fuel Shutoff Valve (Fuel Spar Valve) Position
Aviation Regulations (14 CFR part 39) as Company Model 737–600, –700, –700C,
follows: Indication Operational Check,’’ by
–800, –900, and –900ER series airplanes,
incorporating the information specified in
certificated in any category.
PART 39—AIRWORTHINESS figure 1 to paragraph (g) of this AD into the
DIRECTIVES (d) Subject Airworthiness Limitations Section of the
Air Transport Association (ATA) of Instructions for Continued Airworthiness.
■ 1. The authority citation for part 39 America Code 2823, Fuel Selector/Shutoff The initial compliance time for
continues to read as follows: Valve. accomplishing the actions specified in 28–
Authority: 49 U.S.C. 106(g), 40113, 44701. (e) Unsafe Condition AWL–MOV is within 10 days after
accomplishing the maintenance or inspection
§ 39.13 [Amended] This AD was prompted by reports of program revision required by this paragraph.
latently failed fuel shutoff valves discovered
■ 2. The FAA amends § 39.13 by during fuel filter replacement. We are issuing
removing Airworthiness Directive (AD) this AD to detect and correct latent failures
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, –700C, Engine Fuel Shutoff Valve (Fuel Spar Valve) Po-
–800, –900, and sition Indication Operational Check.
–900ER series air-
planes.
INTERVAL NOTE: The APPLICABILITY NOTE: Concern: The fuel spar valve actuator design
operational check is Only applies to air- can result in airplanes operating with a failed
not required on days planes with a fuel fuel spar valve actuator that is not reported. A
when the airplane is spar valve actuator latently failed fuel spar valve actuator could
not used in revenue having part number prevent fuel shutoff to an engine. In the event
service. MA20A2027 of certain engine fires, the potential exists for
The check must be (S343T003–56) or an engine fire to be uncontrollable.
done before further MA30A1001 Perform one of the following checks of the en-
flight once the air- (S343T003–66) in- gine fuel spar valve position (unless checked
plane is returned to stalled at the engine by the flightcrew in a manner approved by the
revenue service. fuel spar valve posi- principal operations inspector):
tions. 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 CON-
TROL STAND is moved to the CUTOFF posi-
tion, verify the SPAR VALVE CLOSED indica-
tion 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).
asabaliauskas on DSK5VPTVN1PROD with RULES
2. Do an operational check of the right engine
fuel spar valve actuator.
a. As the ENG 2 START LEVER on the CON-
TROL STAND is moved to the CUTOFF posi-
tion, verify the SPAR VALVE CLOSED indica-
tion light on the OVERHEAD PANEL for No. 2
Engine changes from OFF to BRIGHT then
DIM.
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![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 prop-
erly.
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 en-
gine strut. Access is through access panel
521BB on the left wing leading edge.
a. Verify the manual override handle on the en-
gine 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 actu-
ator 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 en-
gine 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 DEPARTMENT OF HOMELAND
After accomplishment of the maintenance For more information about this AD, SECURITY
or inspection program revision required by contact Rebel Nichols, Aerospace Engineer,
paragraph (g) of this AD, no alternative Propulsion Branch, ANM–140S, FAA, Seattle U.S. Customs and Border Protection
actions (e.g., inspections) or intervals may be Aircraft Certification Office, 1601 Lind
used unless the actions or intervals are Avenue SW., Renton, WA 98057–3356; DEPARTMENT OF THE TREASURY
approved as an alternative method of phone: 425–917–6509; fax: 425–917–6590;
compliance (AMOC) in accordance with the email: rebel.nichols@faa.gov. 19 CFR Parts 4, 7, 10, 12, 18, 19, 24,
procedures specified in paragraph (i)(1) of 54, 102, 113, 123, 125, 128, 132, 134,
this AD. (k) Material Incorporated by Reference 141, 142, 143, 144, 145, 146, 148, 151,
(i) Alternative Methods of Compliance None. 152, 158, 163, 174, 181, and 191
(AMOCs) Issued in Renton, Washington, on October [CBP Dec. No. 15–14; USCBP–2015–0045]
(1) The Manager, Seattle Aircraft 16, 2015.
Certification Office (ACO), FAA, has the Jeffrey E. Duven, RIN 1515–AE03
authority to approve AMOCs for this AD, if Manager, Transport Airplane Directorate,
requested using the procedures found in 14 Automated Commercial Environment
Aircraft Certification Service.
CFR 39.19. In accordance with 14 CFR 39.19, (ACE) Filings for Electronic Entry/Entry
[FR Doc. 2015–26992 Filed 10–23–15; 8:45 am]
send your request to your principal inspector Summary (Cargo Release and Related
or local Flight Standards District Office, as BILLING CODE 4910–13–P Entry); Correction
appropriate. If sending information directly
to the manager of the ACO, send it to the AGENCY: U.S. Customs and Border
attention of the person identified in Protection, Department of Homeland
asabaliauskas on DSK5VPTVN1PROD with RULES
paragraph (j) of this AD. Information may be Security; Department of the Treasury.
emailed to: 9-ANM-Seattle-ACO-AMOC- ACTION: Interim final rule; correction.
Requests@faa.gov.
(2) Before using any approved AMOC, SUMMARY: U.S. Customs and Border
notify your appropriate principal inspector, Protection (CBP) published an Interim
or lacking a principal inspector, the manager Final Rule (CBP Dec. 15–14) on October
of the local flight standards district office/ 13, 2015, in the Federal Register, which
certificate holding district office. amends the CBP regulations to reflect
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Document Created: 2018-02-27 08:56:22
Document Modified: 2018-02-27 08:56:22
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule; request for comments. | |
| Dates | This AD is effective October 28, 2015. | |
| 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: [email protected] | |
| FR Citation | 80 FR 65130 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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