Airworthiness Directives; The Boeing Company Airplanes, 65130-65134 [2015-26992]
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65130
Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations
Alert Service Bulletin No. 76–67–57, Basic
Issue, dated September 10, 2015, illustrate
slippage marks across a pushrod tube and
jamnut.
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2015–19–51 Sikorsky Aircraft
Corporation: Amendment 39–18300; Docket
No. FAA–2015–3940; Directorate Identifier
2015–SW–065–AD.
(a) Applicability
This AD applies to Model S–76A, S–76B,
S–76C, and S–76D helicopters with main
rotor (M/R) servo input control pushrod
(pushrod) assembly part number (P/N)
76400–00034–059 or tail rotor (T/R) pushrod
assembly P/N 76400–00014–071 installed,
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
loose jamnut. This condition could result in
failure of a pushrod assembly, loss of M/R or
T/R flight control, and subsequent loss of
control of the helicopter.
(c) Effective Date
This AD becomes effective November 10,
2015 to all persons except those persons to
whom it was made immediately effective by
Emergency AD 2015–19–51, issued on
September 14, 2015, which contains the
requirements of this AD.
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(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
Within five hours time-in-service:
(1) Inspect each pushrod end to determine
whether a 0.020 inch diameter lockwire can
pass through the inspection hole.
(i) If the lockwire passes through the
inspection hole, replace the pushrod
assembly.
(ii) If the lockwire does not pass through
the inspection hole, inspect the jamnut to
determine whether it is seated against the
pushrod and whether it can be turned with
finger pressure. If the jamnut is not seated
against the pushrod or can be turned with
finger pressure, replace the pushrod
assembly.
(2) Apply two slippage marks across each
pushrod tube and jamnut as follows:
(i) Clean the area where a slippage mark is
to be applied.
(ii) Apply two slippage marks across the
pushrod tube and jamnut, parallel and on
opposite sides of each other. Each slippage
mark must extend at least 0.5 inch onto the
pushrod tube and must not cover the
inspection hole. Figures 2 and 4 of Sikorsky
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(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Boston Aircraft
Certification Office, FAA, may approve
AMOCs for this AD. Send your proposal to:
Blaine Williams, Aerospace Engineer, Boston
Aircraft Certification Office, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, Massachusetts
01803; telephone (781) 238–7161; email
blaine.williams@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
(g) Additional Information
Sikorsky Alert Service Bulletin No. 76–67–
57, Basic Issue, dated September 10, 2015,
which is not incorporated by reference,
contains additional information about the
subject of this AD. For service information
identified in this AD, contact Sikorsky
Aircraft Corporation, Customer Service
Engineering, 124 Quarry Road, Trumbull, CT
06611; telephone 1–800–Winged–S or 203–
416–4299; email sikorskywcs@sikorsky.com.
You may review a copy of the service
information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101
Hillwood Pkwy, Room 6N–321, Fort Worth,
TX 76177.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 2700, Flight Control System.
Issued in Fort Worth, Texas, on October 9,
2015.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2015–26949 Filed 10–23–15; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
PO 00000
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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
https://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.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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
65131
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 https://
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
Action
Labor cost
Incorporating Airworthiness Limitation ............
1 work-hour × $85 per 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
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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
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Cost per
product
Parts cost
$0
$85
Cost on U.S.
operators
$105,740
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
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.
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
2015–19–03, Amendment 39–18266 (80
FR 55527, September 16, 2015), and
adding the following new AD:
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
■
(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.
28–AWL–MOV ........................
Task
ALI
Interval
Applicability
Description
DAILY ............................
737–600, –700, –700C,
–800, –900, and
–900ER series airplanes.
APPLICABILITY NOTE:
Only applies to airplanes with a fuel
spar valve actuator
having part number
MA20A2027
(S343T003–56) or
MA30A1001
(S343T003–66) installed at the engine
fuel spar valve positions.
Engine Fuel Shutoff Valve (Fuel Spar Valve) Position Indication Operational Check.
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INTERVAL NOTE: The
operational check is
not required on days
when the airplane is
not used in revenue
service.
The check must be
done before further
flight once the airplane is returned to
revenue service.
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Concern: The fuel spar valve actuator design
can result in airplanes operating with a failed
fuel spar valve actuator that is not reported. A
latently failed fuel spar valve actuator could
prevent fuel shutoff to an engine. In the event
of certain engine fires, 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.
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65133
FIGURE 1 TO PARAGRAPH (g) OF THIS AD—ENGINE FUEL SHUTOFF VALVE (FUEL SPAR VALVE) POSITION INDICATION
OPERATIONAL CHECK—Continued
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AWL No.
Task
Interval
Applicability
Description
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.
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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 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
(j) Related Information
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.
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.
None.
asabaliauskas on DSK5VPTVN1PROD with RULES
(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-AMOCRequests@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.
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(k) Material Incorporated by Reference
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
PO 00000
DEPARTMENT OF HOMELAND
SECURITY
U.S. Customs and Border Protection
DEPARTMENT OF THE TREASURY
19 CFR Parts 4, 7, 10, 12, 18, 19, 24,
54, 102, 113, 123, 125, 128, 132, 134,
141, 142, 143, 144, 145, 146, 148, 151,
152, 158, 163, 174, 181, and 191
[CBP Dec. No. 15–14; USCBP–2015–0045]
RIN 1515–AE03
Automated Commercial Environment
(ACE) Filings for Electronic Entry/Entry
Summary (Cargo Release and Related
Entry); Correction
U.S. Customs and Border
Protection, Department of Homeland
Security; Department of the Treasury.
ACTION: Interim final rule; correction.
AGENCY:
U.S. Customs and Border
Protection (CBP) published an Interim
Final Rule (CBP Dec. 15–14) on October
13, 2015, in the Federal Register, which
amends the CBP regulations to reflect
SUMMARY:
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]]>Agencies
[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]
-----------------------------------------------------------------------
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 https://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 https://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 https://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):
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).
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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
