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ADs updated daily at www.Tdata.com
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| 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 al-
ready 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, Valve (Fuel Spar
-900, and Valve) Position
-900ER series Indication Operational
airplanes. Check.
INTERVAL APPLICABILITY Concern: The fuel spar
NOTE: The NOTE: Only valve actuator design
operational applies to can result in
check is not airplanes with airplanes operating
required on a fuel spar with a failed fuel
days when valve actuator spar valve actuator
the airplane having part that is not reported.
is not used number A latently failed fuel
in revenue MA20A2027 spar valve actuator
service. The (S343T003-56) could prevent fuel
check must or MA30A1001 shutoff to an engine.
be done be- (S343T003-66) In the event of
fore further installed at certain engine fires,
flight once the engine fuel the potential exists
the airplane spar valve for an engine fire to
is returned positions. be uncontrollable.
to revenue Perform one of the
service. 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.
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.
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 in-
spector, 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.
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.
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