Airworthiness Directives; The Boeing Company Airplanes

 
CONTENT

Federal Register, Volume 80 Issue 206 (Monday, October 26, 2015)

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.

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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

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Cost per Cost on U.S.

Action Labor cost Parts cost product operators

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Incorporating Airworthiness Limitation 1 work-hour x $85 per $0 $85 $105,740

hour = $85.

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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

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    AWL No. Task Interval Applicability Description

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    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):

    1. Operational Check

    during engine

    shutdown.

  3. Do an operational

    check of the left

    engine fuel spar valve

    actuator.

    1. 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.

    2. 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).

  4. Do an operational

    check of the right

    engine fuel spar valve

    actuator.

    1. 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.

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    2. If the test fails

      (bright light fails to

      illuminate), before

      further flight, repair

      faults as required

      (refer to Boeing AMM

      28-22-11).

      1. Operational check

      during engine start.

  5. Do an operational

    check of the left

    engine fuel spar valve

    actuator.

    1. 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.

    2. If the test fails

      (bright light fails to

      illuminate), before

      further flight, repair

      faults as required

      (refer to Boeing AMM

      28-22-11).

  6. Do an operational

    check of the right

    engine fuel spar valve

    actuator.

    1. 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.

    2. If the test fails

      (bright light fails to

      illuminate), before

      further flight, repair

      faults as required

      (refer to Boeing AMM

      28-22-11).

      1. Operational check

      without engine

      operation.

  7. Supply electrical

    power to airplane

    using standard

    practices.

  8. Make sure No. 1 and

    No. 2 Engine FIRE

    switches on the Aft

    Electronic Panel are

    in the NORMAL (IN)

    position.

  9. Make sure No. 1 and

    No. 2 Engine Start

    Switches on the

    Forward Overhead Panel

    are in the OFF or AUTO

    position.

  10. Do an operational

    check to the left

    engine fuel spar valve

    actuator.

    1. 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.

    2. Move ENG 1 START

      LEVER on the CONTROL

      STAND to the CUTOFF

      position.

    3. Verify the SPAR

      VALVE CLOSED

      indication light on

      the OVERHEAD PANEL for

      No. 1 Engine changes

      from OFF to BRIGHT

      then DIM.

    4. If the test fails

      (bright light fails to

      illuminate), before

      further flight, repair

      faults as required

      (refer to Boeing AMM

      28-22-11).

  11. Do an operational

    check of the right

    engine fuel spar valve

    actuator.

    1. 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.

    2. Move ENG 2 START

      LEVER on the CONTROL

      STAND to the CUTOFF

      position.

    3. Verify the SPAR

      VALVE CLOSED

      indication light on

      the OVERHEAD PANEL for

      No.2 Engine changes

      from OFF to BRIGHT

      then DIM.

    4. If the test fails

      (bright light fails to

      illuminate), before

      further flight, repair

      faults as required

      (refer to Boeing AMM

      28-22-11).

      1. 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.

  12. 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.

  13. 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.

    1. Verify the manual

      override handle on the

      engine fuel spar valve

      actuator is in the

      CLOSED position.

    2. Repair or replace

      any engine fuel spar

      valve actuator that is

      not in the CLOSED

      position (refer to

      Boeing AMM 28-22-11).

  14. 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.

  15. 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.

    1. Verify the manual

      override handle on the

      engine fuel spar valve

      actuator is in the

      CLOSED position.

    2. Repair or replace

      any engine fuel spar

      valve actuator that is

      not in the CLOSED

      position (refer to

      Boeing AMM 28-22-11).

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      (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