Airworthiness Directives; The Boeing Company Airplanes, 65121-65126 [2015-26983]
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65121
Rules and Regulations
Federal Register
Vol. 80, No. 206
Monday, October 26, 2015
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Examining the AD Docket
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
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
https://www.regulations.gov. Follow the
instructions for submitting comments.
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SUMMARY:
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• 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.
You may examine the AD docket on
the Internet at https://
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.
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
SUPPLEMENTARY INFORMATION:
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.
Discussion
AD Requirements
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.
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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
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‘‘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 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 450
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 .................
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.
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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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Cost per
product
Parts cost
$0
Cost on U.S.
operators
$85
(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.
(c) Applicability
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
$38,250
Air Transport Association (ATA) of
America Code 28, Fuel.
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
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 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).
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(d) Subject
(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
1. The authority citation for part 39
continues to read as follows:
■
§ 39.13
This AD applies to all The Boeing
Company Model 767–200, –300, –300F, and
–400ER series airplanes, certificated in any
category.
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.
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65123
FIGURE 1 TO PARAGRAPH (g) OF THIS AD: ENGINE FUEL SHUTOFF VALVE (FUEL SPAR VALVE) POSITION INDICATION
OPERATIONAL CHECK
AWL No.
Task
28–AWL–ENG ...
ALI
Interval
Applicability
Description
DAILY .................................
767–200, –300, and –300F
airplanes.
APPLICABILITY NOTE: Applies to airplanes with an
actuator installed at the
engine fuel spar valve
position having part number (P/N) MA20A2027
(S343T003–56) or P/N
MA30A1001 (S343T003–
66).
Engine Fuel Shutoff Valve (Fuel Spar Valve) Position
Indication Operational Check.
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/inspection of the
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 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.
b. 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).
2. Do an operational check of the right engine fuel spar
valve actuator.
a. 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.
b. If the test fails (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 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.
b. If the test fails (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 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.
b. If the test fails (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 the airplane using standard practices.
2. Make sure all fuel pump switches on the Overhead
Panel are in the OFF position.
3. 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.
4. Make sure LEFT and RIGHT ENG FIRE switches on
the Aft Aisle Stand are in the NORMAL (IN) position.
5. Make sure L and R ENG START Selector Switches
on the Overhead Panel, are in the OFF position.
6. Do an operational check of the left engine fuel spar
valve actuator.
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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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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
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AWL No.
Task
Interval
Applicability
Description
a. 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.
b. Move L FUEL CONTROL switch on the quadrant
control stand to the CUTOFF position.
c. Verify the left SPAR VALVE disagreement light on
the quadrant control stand illuminates and then goes
off.
d. If the test fails (light fails to illuminate), before further
flight, repair faults as required (refer to Boeing AMM
28–22–11).
7. Do an operational check of the right engine fuel spar
valve actuator.
a. 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.
b. Move R FUEL CONTROL switch on the quadrant
control stand to the CUTOFF position.
c. Verify the right SPAR VALVE disagreement light on
the quadrant control stand illuminates and then goes
off.
d. If the test fails (light fails to illuminate), before further
flight, repair faults as required (refer to Boeing AMM
28–22–11).
8. If the L FWD FUEL BOOST PUMP circuit breaker
was collared in step 3, remove collar and close.
D. 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.
1. 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.
2. 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.
a. Verify the manual override handle on the engine fuel
spar valve actuator is in the CLOSED position.
b. Repair or replace any fuel spar valve actuator that is
not in the CLOSED position (refer to Boeing AMM
28–22–11).
3. 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.
4. 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.
a. Verify the manual override handle on the engine fuel
spar valve actuator is in the CLOSED position.
b. Repair or replace any fuel spar valve actuator that is
not in the CLOSED position (refer to Boeing AMM
28–22–11).
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65125
FIGURE 2 TO PARAGRAPH (G) OF THIS AD: ENGINE FUEL SHUTOFF VALVE (FUEL SPAR VALVE) ACTUATOR INSPECTION
AWL No.
Task
28-AWL-MOV ....
ALI
Interval
Applicability
Description
10 DAYS ............................
767–400ER series airplanes.
APPLICABILITY NOTE: Applies to airplanes with an
actuator installed at the
engine fuel spar valve
position having part number (P/N) MA20A2027
(S343T003–56) or P/N
MA30A1001 (S343T003–
66).
Engine Fuel Shutoff Valve (Fuel Spar Valve) Actuator
Inspection.
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 would prevent fuel shutoff to an engine. In the event of certain engine fires, the 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.
1. 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.
2. Inspect the left engine fuel spar valve actuator located in the left rear spar.
a. Verify the manual override handle on the engine fuel
spar valve actuator is in the CLOSED position.
b. Repair or replace any fuel spar valve actuator that is
not in the CLOSED position (refer to Boeing AMM
28–22–11).
3. 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.
4. Inspect the right engine fuel spar valve actuator located in the right rear spar.
a. Verify the manual override handle on the engine fuel
spar valve actuator is in the CLOSED position.
b. Repair or replace any fuel spar valve actuator that is
not in the CLOSED position (refer to Boeing AMM
28–22–11).
INTERVAL NOTE: The inspection is not required
on days when the airplane is not used in revenue service.
The inspection must be
done before further flight
if it has been 10 or more
calendar days since last
inspection.
FIGURE 3 TO PARAGRAPH (G) OF THIS AD: AUXILIARY POWER UNIT (APU) FUEL SHUTOFF VALVE POSITION INDICATION
OPERATIONAL CHECK
AWL No.
Task
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ALI
Applicability
Description
10 DAYS ............................
ALL .....................................
INTERVAL NOTE: The
operational check is not
required on days when
the airplane is not used
in revenue service. The
operational check must
be done before further
flight with an operational
APU if it has been 10 or
more calendar days since
last check.
28–AWL–APU ...
Interval
APPLICABILITY NOTE: Applies to airplanes with an
actuator installed at the
APU fuel shutoff valve
position having part number (P/N) MA20A2027
(S343T003–56) or
MA30A1001 (S343T003–
66).
APU Fuel Shutoff Valve Position Indication Operational
Check.
Concern: The APU fuel shutoff valve actuator design
can result in airplanes operating with a failed APU
fuel shutoff valve actuator that is not reported. A latently failed APU fuel shutoff valve actuator could
prevent fuel shutoff to the APU. In the event of certain APU fires, the potential exists for an APU fire 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).
A. Do an operational check of the APU fuel shutoff
valve position indication.
1. If the APU is running, unload and shut down the
APU using standard practices.
2. Supply electrical power to the airplane using standard practices.
3. Make sure the APU FIRE switch on the Aft Aisle
Stand is in the NORMAL (IN) position.
4. Make sure there is at least 1,000 lbs (500 kgs) of
fuel in the Left Main Tank.
5. 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.
6. Move the APU Selector switch on the Overhead
Panel to the OFF position.
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FIGURE 3 TO PARAGRAPH (G) OF THIS AD: AUXILIARY POWER UNIT (APU) FUEL SHUTOFF VALVE POSITION INDICATION
OPERATIONAL CHECK—Continued
AWL No.
Task
Interval
Applicability
Description
7. Verify the APU FAULT light on the Overhead Panel
illuminates and then goes off.
8. 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
DEPARTMENT OF TRANSPORTATION
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.
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0933; Directorate
Identifier 2014–NM–098–AD; Amendment
39–18297; AD 2015–21–05]
RIN 2120–AA64
(i) Alternative Methods of Compliance
(AMOCs)
Airworthiness Directives; Fokker
Services B.V. Airplanes
(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.
AGENCY:
(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
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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
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Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
We are adopting a new
airworthiness directive (AD) for all
Fokker Services B.V. Model F.27 Mark
200, 300, 400, 500, 600, and 700
airplanes. This AD was prompted by a
design review, which revealed that no
controlled bonding provisions are
present on a number of critical locations
inside the fuel tank or connected to the
fuel tank wall; and no anti-spray cover
is installed on the fuel shut-off valve
(FSOV) in both wings. This AD requires
installing additional bonding provisions
in the fuel tank, installing an anti-spray
cover on the FSOV, and revising the
airplane maintenance program by
incorporating fuel airworthiness
limitation items and critical design
configuration control limitations. We
are issuing this AD to prevent an
ignition source in the fuel tank vapor
space, which could result in a fuel tank
explosion and consequent loss of the
airplane.
SUMMARY:
This AD becomes effective
November 30, 2015.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2015-0933 or in
person at the Docket Management
Facility, U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC.
DATES:
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1137;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
FOR FURTHER INFORMATION CONTACT:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Fokker Services B.V. Model
F.27 Mark 200, 300, 400, 500, 600, and
700 airplanes. The NPRM published in
the Federal Register on May 4, 2015 (80
FR 25247).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0099, dated April 30,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Fokker
Services B.V. Model F.27 Mark 200, 300,
400, 500, 600, and 700 airplanes. The
MCAI states:
Prompted by an accident * * *, the FAA
published Special Federal Aviation
Regulation (SFAR) 88 [(66 FR 23086, May 7,
2001)], and the Joint Aviation Authorities
(JAA) published Interim Policy INT/POL/25/
12.
The review conducted by Fokker Services
on the Fokker 27 design in response to these
regulations revealed that no controlled
bonding provisions are present on a number
of critical locations, inside the fuel tank or
connected to the fuel tank wall, and no antispray cover is installed on the Fueling ShutOff Valve (FSOV) in both wings.
This condition, if not corrected, could
create an ignition source in the fuel tank
vapour space, possibly resulting in a fuel
tank explosion and consequent loss of the
aeroplane.
To address this potential unsafe condition,
Fokker Services developed a set of bonding
modifications and anti-spray covers, [and]
introduced with Service Bulletin (SB)
SBF27–28–071 Revision 1 (R1), that require
opening of the fuel tank access panels. More
information on this subject can be found in
Fokker Services All Operators Message
AOF27.043#03.
E:\FR\FM\26OCR1.SGM
26OCR1
]]>Agencies
[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]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 /
Rules and Regulations
[[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 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-
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 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 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.
----------------------------------------------------------------------------------------------------------------
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):
A. Operational Check
during engine shutdown.
1. Do an operational
check of the left engine
fuel spar valve
actuator.
a. 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.
b. 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).
2. Do an operational
check of the right
engine fuel spar valve
actuator.
a. 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.
b. If the test fails
(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 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.
b. If the test fails
(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 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.
b. If the test fails
(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 the airplane
using standard
practices.
2. Make sure all fuel
pump switches on the
Overhead Panel are in
the OFF position.
3. 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.
4. Make sure LEFT and
RIGHT ENG FIRE switches
on the Aft Aisle Stand
are in the NORMAL (IN)
position.
5. Make sure L and R ENG
START Selector Switches
on the Overhead Panel,
are in the OFF position.
6. Do an operational
check of the left engine
fuel spar valve
actuator.
[[Page 65124]]
a. 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.
b. Move L FUEL CONTROL
switch on the quadrant
control stand to the
CUTOFF position.
c. Verify the left SPAR
VALVE disagreement light
on the quadrant control
stand illuminates and
then goes off.
d. If the test fails
(light fails to
illuminate), before
further flight, repair
faults as required
(refer to Boeing AMM 28-
22-11).
7. Do an operational
check of the right
engine fuel spar valve
actuator.
a. 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.
b. Move R FUEL CONTROL
switch on the quadrant
control stand to the
CUTOFF position.
c. Verify the right SPAR
VALVE disagreement light
on the quadrant control
stand illuminates and
then goes off.
d. If the test fails
(light fails to
illuminate), before
further flight, repair
faults as required
(refer to Boeing AMM 28-
22-11).
8. If the L FWD FUEL
BOOST PUMP circuit
breaker was collared in
step 3, remove collar
and close.
D. 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.
1. 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.
2. 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.
a. Verify the manual
override handle on the
engine fuel spar valve
actuator is in the
CLOSED position.
b. Repair or replace any
fuel spar valve actuator
that is not in the
CLOSED position (refer
to Boeing AMM 28-22-11).
3. 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.
4. 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.
a. Verify the manual
override handle on the
engine fuel spar valve
actuator is in the
CLOSED position.
b. 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
----------------------------------------------------------------------------------------------------------------
28[dash]AWL[dash]MOV...... 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.
1. 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.
2. Inspect the left
engine fuel spar valve
actuator located in the
left rear spar.
a. Verify the manual
override handle on the
engine fuel spar valve
actuator is in the
CLOSED position.
b. Repair or replace any
fuel spar valve actuator
that is not in the
CLOSED position (refer
to Boeing AMM 28-22-11).
3. 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.
4. Inspect the right
engine fuel spar valve
actuator located in the
right rear spar.
a. Verify the manual
override handle on the
engine fuel spar valve
actuator is in the
CLOSED position.
b. 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).
A. Do an operational
check of the APU fuel
shutoff valve position
indication.
1. If the APU is running,
unload and shut down the
APU using standard
practices.
2. Supply electrical
power to the airplane
using standard
practices.
3. Make sure the APU FIRE
switch on the Aft Aisle
Stand is in the NORMAL
(IN) position.
4. Make sure there is at
least 1,000 lbs (500
kgs) of fuel in the Left
Main Tank.
5. 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.
6. Move the APU Selector
switch on the Overhead
Panel to the OFF
position.
[[Page 65126]]
7. Verify the APU FAULT
light on the Overhead
Panel illuminates and
then goes off.
8. 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
