Airworthiness Directives; The Boeing Company Airplanes
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
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:
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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),
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(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
-
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
-
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):
-
Operational Check
during engine
shutdown.
-
-
Do an operational
check of the left
engine fuel spar valve
actuator.
-
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.
-
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).
-
-
Do an operational
check of the right
engine fuel spar valve
actuator.
-
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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-
If the test fails
(bright light fails to
illuminate), before
further flight, repair
faults as required
(refer to Boeing AMM
28-22-11).
-
Operational check
during engine start.
-
-
-
Do an operational
check of the left
engine fuel spar valve
actuator.
-
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.
-
If the test fails
(bright light fails to
illuminate), before
further flight, repair
faults as required
(refer to Boeing AMM
28-22-11).
-
-
Do an operational
check of the right
engine fuel spar valve
actuator.
-
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.
-
If the test fails
(bright light fails to
illuminate), before
further flight, repair
faults as required
(refer to Boeing AMM
28-22-11).
-
Operational check
without engine
operation.
-
-
-
Supply electrical
power to airplane
using standard
practices.
-
Make sure No. 1 and
No. 2 Engine FIRE
switches on the Aft
Electronic Panel are
in the NORMAL (IN)
position.
-
Make sure No. 1 and
No. 2 Engine Start
Switches on the
Forward Overhead Panel
are in the OFF or AUTO
position.
-
Do an operational
check to the left
engine fuel spar valve
actuator.
-
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.
-
Move ENG 1 START
LEVER on the CONTROL
STAND 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.
-
If the test fails
(bright light fails to
illuminate), before
further flight, repair
faults as required
(refer to Boeing AMM
28-22-11).
-
-
Do an operational
check of the right
engine fuel spar valve
actuator.
-
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.
-
Move ENG 2 START
LEVER on the CONTROL
STAND 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.
-
If the test fails
(bright light fails to
illuminate), before
further flight, repair
faults as required
(refer to Boeing AMM
28-22-11).
-
Perform an
inspection of the
engine fuel spar valve
actuator position.
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NOTE: This inspection
may be used whenever
the SPAR VALVE light
does not function
properly.
-
-
-
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.
-
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.
-
Verify the manual
override handle on the
engine fuel spar valve
actuator is in the
CLOSED position.
-
Repair or replace
any engine fuel spar
valve actuator that is
not in the CLOSED
position (refer to
Boeing AMM 28-22-11).
-
-
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.
-
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.
-
Verify the manual
override handle on the
engine fuel spar valve
actuator is in the
CLOSED position.
-
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
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