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 65121-65126

From the Federal Register Online via the Government Publishing Office www.gpo.gov

FR Doc No: 2015-26983

Page 65121

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

Docket No. FAA-2015-4209; Directorate Identifier 2015-NM-156-AD; Amendment 39-18302; AD 2015-21-09

RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 2015-19-02 for all The Boeing Company Model 767 airplanes. AD 2015-19-02 required revising the maintenance or inspection program to include new airworthiness limitations. This AD continues to require a maintenance or inspection program revision, but with revised language. This AD was prompted by a determination that certain language in the airworthiness limitation was not accurate in AD 2015-19-02. We are issuing this AD to detect and correct latent failures of the fuel shutoff valve to the engine and auxiliary power unit (APU), which could result in the inability to shut off fuel to the engine and APU and, in case of certain fires, an uncontrollable fire that could lead to structural failure.

DATES: This AD is effective October 28, 2015.

We must receive any comments on this AD by December 10, 2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:

Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

Fax: 202-493-2251.

Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-

4209; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Rebel Nichols, Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-

6509; fax: 425-917-6590; email: rebel.nichols@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

On September 7, 2015, we issued AD 2015-19-02, Amendment 39-18265 (80 FR 55512, September 16, 2015), for all The Boeing Company Model 767 airplanes. AD 2015-19-02 required revising the maintenance or inspection program to include new airworthiness limitations. AD 2015-

19-02 resulted from reports of latently failed fuel shutoff valves discovered during fuel filter replacement. We issued AD 2015-19-02 to detect and correct latent failures of the fuel shutoff valve to the engine and APU, which could result in the inability to shut off fuel to the engine and APU and, in case of certain fires, an uncontrollable fire that could lead to structural failure.

Actions Since AD 2015-19-02, Amendment 39-18265 (80 FR 55512, September 16, 2015), Was Issued

Since we issued AD 2015-19-02, Amendment 39-18265 (80 FR 55512, September 16, 2015), we have determined that extraneous language was included in two locations of the text of the airworthiness limitations specified in AD 2015-19-02. In paragraph C.7.a. of the ``Description'' column of figure 1 to paragraph (g) of AD 2015-19-02, the text ``or the APU selector switch on the overhead panel is in the ON position'' is not relevant to the actions specified in that paragraph. In paragraph A.5. of the ``Description'' column of figure 3 to paragraph (g) of AD 2015-19-02, the text ``the FUEL CONTROL switch is in the RUN position or'' is not relevant to the actions specified in that paragraph.

We have determined that the language must be corrected to avoid any confusion in the paragraphs of the airworthiness limitation. We are issuing this AD to detect and correct latent failures of the fuel shutoff valve to the engine and APU, which could result in the inability to shut off fuel to the engine and APU and, in case of certain fires, an uncontrollable fire that could lead to structural failure.

FAA's Determination

We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design.

AD Requirements

This AD requires revising the maintenance or inspection program to include new airworthiness limitations.

Interim Action

We consider this AD interim action. The manufacturer is currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, and available, we might consider additional rulemaking.

FAA's Justification and Determination of the Effective Date

We are superseding AD 2015-19-02, Amendment 39-18265 (80 FR 55512, September 16, 2015), to correct inaccurate terminology in the

Page 65122

``Description'' column of figure 1 to paragraph (g) of AD 2015-19-02 and figure 3 to paragraph (g) of AD 2015-19-02. We have made no other changes to the requirements published in AD 2015-19-02. We have determined that the changes impose no additional burden on any operator. Therefore, we find that notice and opportunity for prior public comment are unnecessary and that good cause exists for making this amendment effective in less than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include the Docket Number FAA-2015-4209 and Directorate Identifier 2015-NM-156-

AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments.

We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD.

Costs of Compliance

We estimate that this AD affects 450 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:

Estimated Costs

----------------------------------------------------------------------------------------------------------------

Cost per Cost on U.S.

Action Labor cost Parts cost product operators

----------------------------------------------------------------------------------------------------------------

Incorporating Airworthiness Limitation 1 work-hour x $85 per $0 $85 $38,250

hour = $85.

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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),

(3) Will not affect intrastate aviation in Alaska, and

(4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0

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

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

    Sec. 39.13 Amended

    0

  2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2015-19-02, Amendment 39-18265 (80 FR 55512, September 16, 2015), and adding the following new AD:

    2015-21-09 The Boeing Company: Amendment 39-18302; Docket No. FAA-

    2015-4209; Directorate Identifier 2015-NM-156-AD.

    (a) Effective Date

    This AD is effective October 28, 2015.

    (b) Affected ADs

    This AD replaces AD 2015-19-02, Amendment 39-18265 (80 FR 55512, September 16, 2015).

    (c) Applicability

    This AD applies to all The Boeing Company Model 767-200, -300, -

    300F, and -400ER series airplanes, certificated in any category.

    (d) Subject

    Air Transport Association (ATA) of America Code 28, Fuel.

    (e) Unsafe Condition

    This AD was prompted by reports of latently failed fuel shutoff valves discovered during fuel filter replacement. We are issuing this AD to detect and correct latent failures of the fuel shutoff valve to the engine and auxiliary power unit (APU), which could result in the inability to shut off fuel to the engine and APU and, in case of certain fires, an uncontrollable fire that could lead to structural failure.

    (f) Compliance

    Comply with this AD within the compliance times specified, unless already done.

    (g) Revision of Maintenance or Inspection Program

    Within 30 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to add airworthiness limitation numbers 28-AWL-ENG, 28-AWL-MOV, and 28-AWL-

    APU, by incorporating the information specified in figure 1, figure 2, and figure 3 to paragraph (g) of this AD into the Airworthiness Limitations Section of the Instructions for Continued Airworthiness. The initial compliance time for accomplishing the actions specified in figure 1, figure 2, and figure 3 to paragraph (g) of this AD is within 10 days after accomplishing the maintenance or inspection program revision required by this paragraph.

    Page 65123

    Figure 1 to Paragraph (g) of This AD: Engine Fuel Shutoff Valve (Fuel Spar Valve) Position Indication

    Operational Check

    ----------------------------------------------------------------------------------------------------------------

    AWL No. Task Interval Applicability Description

    ----------------------------------------------------------------------------------------------------------------

    28-AWL-ENG................ ALI DAILY............... 767-200, -300, and - Engine Fuel Shutoff Valve

    300F airplanes. (Fuel Spar Valve)

    Position Indication

    Operational Check.

    INTERVAL NOTE: The APPLICABILITY NOTE: Concern: The fuel spar

    operational check Applies to valve actuator design

    is not required on airplanes with an can result in airplanes

    days when the actuator installed operating with a failed

    airplane is not at the engine fuel fuel spar valve actuator

    used in revenue spar valve position that is not reported. A

    service. having part number latently failed fuel

    The check must be (P/N) MA20A2027 spar valve actuator

    done before further (S343T003-56) or P/ could prevent fuel

    flight once the N MA30A1001 shutoff to an engine. In

    airplane is (S343T003-66). the event of certain

    returned to revenue engine fires, the

    service. potential exists for an

    engine fire to be

    uncontrollable.

    Perform one of the

    following checks/

    inspection of the fuel

    spar valve position

    (unless checked by the

    flightcrew in a manner

    approved by the

    principal operations

    inspector):

    1. Operational Check

    during engine shutdown.

  3. Do an operational

    check of the left engine

    fuel spar valve

    actuator.

    1. As the L FUEL CONTROL

      switch on the quadrant

      control stand is moved

      to the CUTOFF position,

      verify the left SPAR

      VALVE disagreement light

      on the quadrant control

      stand illuminates and

      then goes off.

    2. If the test fails

      (light fails to

      illuminate), before

      further flight, repair

      faults as required

      (refer to Boeing

      airplane maintenance

      manual (AMM) 28-22-11).

  4. Do an operational

    check of the right

    engine fuel spar valve

    actuator.

    1. As the R FUEL CONTROL

      switch on the quadrant

      control stand is moved

      to the CUTOFF position,

      verify the right SPAR

      VALVE disagreement light

      on the quadrant control

      stand illuminates and

      then goes off.

    2. If the test fails

      (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 L FUEL CONTROL

      switch on the quadrant

      control stand is moved

      to the RUN (or RICH)

      position, verify the

      left SPAR VALVE

      disagreement light on

      the quadrant control

      stand illuminates and

      then goes off.

    2. If the test fails

      (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 R FUEL CONTROL

      switch on the quadrant

      control stand is moved

      to the RUN (or RICH)

      position, verify the

      right SPAR VALVE

      disagreement light on

      the quadrant control

      stand illuminates and

      then goes off.

    2. If the test fails

      (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 the airplane

    using standard

    practices.

  8. Make sure all fuel

    pump switches on the

    Overhead Panel are in

    the OFF position.

  9. If the auxiliary power

    unit (APU) is running,

    open and collar the L

    FWD FUEL BOOST PUMP

    (C00372) circuit breaker

    on the Main Power

    Distribution Panel.

  10. Make sure LEFT and

    RIGHT ENG FIRE switches

    on the Aft Aisle Stand

    are in the NORMAL (IN)

    position.

  11. Make sure L and R ENG

    START Selector Switches

    on the Overhead Panel,

    are in the OFF position.

  12. Do an operational

    check of the left engine

    fuel spar valve

    actuator.

    Page 65124

    1. Move L FUEL CONTROL

      switch on the quadrant

      control stand to the RUN

      position and wait

      approximately 10

      seconds.

      NOTE: It is normal under

      this test condition for

      the ENG VALVE

      disagreement light on

      the quadrant control

      stand to stay

      illuminated.

    2. Move L FUEL CONTROL

      switch on the quadrant

      control stand to the

      CUTOFF position.

    3. Verify the left SPAR

      VALVE disagreement light

      on the quadrant control

      stand illuminates and

      then goes off.

    4. If the test fails

      (light fails to

      illuminate), before

      further flight, repair

      faults as required

      (refer to Boeing AMM 28-

      22-11).

  13. Do an operational

    check of the right

    engine fuel spar valve

    actuator.

    1. Move R FUEL CONTROL

      switch on the quadrant

      control stand to the RUN

      position and wait

      approximately 10 seconds

      once the FUEL CONTROL

      switch is in the RUN

      position.

      NOTE: It is normal under

      this test condition for

      the ENG VALVE

      disagreement light on

      the quadrant control

      stand to stay

      illuminated.

    2. Move R FUEL CONTROL

      switch on the quadrant

      control stand to the

      CUTOFF position.

    3. Verify the right SPAR

      VALVE disagreement light

      on the quadrant control

      stand illuminates and

      then goes off.

    4. If the test fails

      (light fails to

      illuminate), before

      further flight, repair

      faults as required

      (refer to Boeing AMM 28-

      22-11).

  14. If the L FWD FUEL

    BOOST PUMP circuit

    breaker was collared in

    step 3, remove collar

    and close.

    1. Perform an inspection

    of the fuel spar valve

    actuator position.

    NOTE: This inspection may

    be most useful whenever

    the SPAR VALVE light

    does not function

    properly.

  15. Make sure the L FUEL

    CONTROL switch on the

    quadrant control stand

    is in the CUTOFF

    position.

    NOTE: It is not necessary

    to cycle the FUEL

    CONTROL switch to do

    this inspection.

  16. Inspect the left

    engine fuel spar valve

    actuator located in the

    left rear spar.

    NOTE: The Fuel Spar Valve

    actuators are located

    behind main gear doors

    on the rear spar.

    1. Verify the manual

      override handle on the

      engine fuel spar valve

      actuator is in the

      CLOSED position.

    2. Repair or replace any

      fuel spar valve actuator

      that is not in the

      CLOSED position (refer

      to Boeing AMM 28-22-11).

  17. Make sure the R FUEL

    CONTROL switch on the

    quadrant control stand

    is in the CUTOFF

    position.

    NOTE: It is not necessary

    to cycle the FUEL

    CONTROL switch to do

    this inspection.

  18. Inspect the right

    engine fuel spar valve

    actuator located in the

    right rear spar.

    NOTE: The Fuel Spar Valve

    actuators are located

    behind main gear doors

    on the rear spar.

    1. Verify the manual

      override handle on the

      engine fuel spar valve

      actuator is in the

      CLOSED position.

    2. Repair or replace any

      fuel spar valve actuator

      that is not in the

      CLOSED position (refer

      to Boeing AMM 28-22-11).

      ----------------------------------------------------------------------------------------------------------------

      Page 65125

      Figure 2 to Paragraph (g) of This AD: Engine Fuel Shutoff Valve (Fuel Spar Valve) Actuator Inspection

      ----------------------------------------------------------------------------------------------------------------

      AWL No. Task Interval Applicability Description

      ----------------------------------------------------------------------------------------------------------------

      28dashAWLdashMOV...... ALI 10 DAYS............. 767-400ER series Engine Fuel Shutoff Valve

      airplanes. (Fuel Spar Valve)

      Actuator Inspection.

      INTERVAL NOTE: The APPLICABILITY NOTE: Concern: The fuel spar

      inspection is not Applies to valve actuator design

      required on days airplanes with an can result in airplanes

      when the airplane actuator installed operating with a failed

      is not used in at the engine fuel fuel spar valve actuator

      revenue service. spar valve position that is not reported. A

      The inspection must having part number latently failed fuel

      be done before (P/N) MA20A2027 spar valve actuator

      further flight if (S343T003-56) or P/ would prevent fuel

      it has been 10 or N MA30A1001 shutoff to an engine. In

      more calendar days (S343T003-66). the event of certain

      since last engine fires, the

      inspection. potential exists for an

      engine fire to be

      uncontrollable.

      Perform an inspection of

      the fuel spar valve

      actuator position.

      NOTE: The fuel spar valve

      actuators are located

      behind main gear doors

      on the rear spar.

  19. Make sure the L FUEL

    CONTROL switch on the

    quadrant control stand

    is in the CUTOFF

    position.

    NOTE: It is not necessary

    to cycle the FUEL

    CONTROL switch to do

    this inspection.

  20. Inspect the left

    engine fuel spar valve

    actuator located in the

    left rear spar.

    1. Verify the manual

      override handle on the

      engine fuel spar valve

      actuator is in the

      CLOSED position.

    2. Repair or replace any

      fuel spar valve actuator

      that is not in the

      CLOSED position (refer

      to Boeing AMM 28-22-11).

  21. Make sure the R FUEL

    CONTROL switch on the

    quadrant control stand

    is in the CUTOFF

    position.

    NOTE: It is not necessary

    to cycle the FUEL

    CONTROL switch to do

    this inspection.

  22. Inspect the right

    engine fuel spar valve

    actuator located in the

    right rear spar.

    1. Verify the manual

      override handle on the

      engine fuel spar valve

      actuator is in the

      CLOSED position.

    2. Repair or replace any

      fuel spar valve actuator

      that is not in the

      CLOSED position (refer

      to Boeing AMM 28-22-11).

      ----------------------------------------------------------------------------------------------------------------

      Figure 3 to Paragraph (g) of This AD: Auxiliary Power Unit (APU) Fuel Shutoff Valve Position Indication

      Operational Check

      ----------------------------------------------------------------------------------------------------------------

      AWL No. Task Interval Applicability Description

      ----------------------------------------------------------------------------------------------------------------

      28-AWL-APU................ ALI 10 DAYS............. ALL................. APU Fuel Shutoff Valve

      Position Indication

      Operational Check.

      INTERVAL NOTE: The APPLICABILITY NOTE: Concern: The APU fuel

      operational check Applies to shutoff valve actuator

      is not required on airplanes with an design can result in

      days when the actuator installed airplanes operating with

      airplane is not at the APU fuel a failed APU fuel

      used in revenue shutoff valve shutoff valve actuator

      service. The position having that is not reported. A

      operational check part number (P/N) latently failed APU fuel

      must be done before MA20A2027 (S343T003- shutoff valve actuator

      further flight with 56) or MA30A1001 could prevent fuel

      an operational APU (S343T003-66). shutoff to the APU. In

      if it has been 10 the event of certain APU

      or more calendar fires, the potential

      days since last exists for an APU fire

      check. to be uncontrollable

      Perform the operational

      check of the APU fuel

      shutoff valve position

      indication (unless

      checked by the

      flightcrew in a manner

      approved by the

      principal operations

      inspector).

      1. Do an operational

      check of the APU fuel

      shutoff valve position

      indication.

  23. If the APU is running,

    unload and shut down the

    APU using standard

    practices.

  24. Supply electrical

    power to the airplane

    using standard

    practices.

  25. Make sure the APU FIRE

    switch on the Aft Aisle

    Stand is in the NORMAL

    (IN) position.

  26. Make sure there is at

    least 1,000 lbs (500

    kgs) of fuel in the Left

    Main Tank.

  27. Move APU Selector

    switch on the Overhead

    Panel to the ON position

    and wait approximately

    10 seconds once the APU

    selector switch on the

    overhead panel is in the

    ON position.

  28. Move the APU Selector

    switch on the Overhead

    Panel to the OFF

    position.

    Page 65126

  29. Verify the APU FAULT

    light on the Overhead

    Panel illuminates and

    then goes off.

  30. If the test fails

    (light fails to

    illuminate), before

    further flight requiring

    APU availability, repair

    faults as required

    (refer to Boeing AMM 28-

    25-02).

    NOTE: Dispatch may be

    permitted per MMEL 28-25-

    02 if APU is not

    required for flight.

    ----------------------------------------------------------------------------------------------------------------

    (h) No Alternative Actions or Intervals

    After accomplishment of the maintenance or inspection program revision required by paragraph (g) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (i)(1) of this AD.

    (i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO) FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (j) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.

    (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office.

    (j) Related Information

    For more information about this AD, contact Rebel Nichols, Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6509; fax: 425-917-6590; email: rebel.nichols@faa.gov.

    (k) Material Incorporated by Reference

    None.

    Issued in Renton, Washington, on October 16, 2015.

    Jeffrey E. Duven,

    Manager, Transport Airplane Directorate, Aircraft Certification Service.

    FR Doc. 2015-26983 Filed 10-23-15; 8:45 am

    BILLING CODE 4910-13-P