Airworthiness Directives; Boeing Model 747-400, 747-400D, and 747-400F Series Airplanes, 6404-6408 [E6-1682]
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Federal Register / Vol. 71, No. 26 / Wednesday, February 8, 2006 / Proposed Rules
Optional Terminating Action
(h) Accomplishing the preventive
modification of the wing-to-body fairing
panels in accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 777–53A0044, dated July 28,
2005, terminates the repetitive inspections
required by paragraph (f) of this AD for the
modified area only.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Seattle ACO, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane.
Issued in Renton, Washington, on January
30, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–1681 Filed 2–7–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23803; Directorate
Identifier 2005–NM–238–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–400, 747–400D, and 747–
400F Series Airplanes
Federal Aviation
Administration, DOT.
ACTION: Notice of proposed rulemaking.
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AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all Boeing
Model 747–400, –400D, and –400F
series airplanes. The existing AD
currently requires revising the airplane
flight manual (AFM) to require the
flightcrew to maintain certain minimum
fuel levels in the center fuel tanks, and
to prohibit the use of the horizontal
stabilizer fuel tank. This proposed AD
would require installing new integrated
display software in the integrated
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display units and electronic flight
instrument system/engine indication
and crew alerting system interface units
(EIUs) of the flight deck. This proposed
AD also would require revising the AFM
to include procedures to prevent dry
operation of the center wing and
horizontal stabilizer fuel tanks; for
maintaining minimum fuel levels; and
for de-fueling fuel tanks. For certain
airplanes, the proposed AD also requires
removing G13 pin ground wires of a
certain wire integration unit of the EIUs
at certain connector locations. This
proposed AD results from fuel system
reviews conducted by the manufacturer.
We are proposing this AD to reduce the
potential for ignition sources inside fuel
tanks, which, in combination with
flammable fuel vapors, could result in
fuel tank explosions and consequent
loss of the airplane.
DATES: We must receive comments on
this proposed AD by March 27, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT:
Sulmo Mariano, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6501; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘Docket No. FAA–2006–23803;
Directorate Identifier 2005–NM–238–
AD’’ at the beginning of your comments.
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We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or may visit https://
dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
Discussion
The FAA has examined the
underlying safety issues involved in fuel
tank explosions on several large
transport airplanes, including the
adequacy of existing regulations, the
service history of airplanes subject to
those regulations, and existing
maintenance practices for fuel tank
systems. As a result of those findings,
we issued a regulation titled ‘‘Transport
Airplane Fuel Tank System Design
Review, Flammability Reduction and
Maintenance and Inspection
Requirements’’ (67 FR 23086, May 7,
2001). In addition to new airworthiness
standards for transport airplanes and
new maintenance requirements, this
rule included Special Federal Aviation
Regulation No. 88 (‘‘SFAR 88,’’
Amendment 21–78, and subsequent
Amendments 21–82 and 21–83).
Among other actions, SFAR 88
requires certain type design (i.e., type
certificate (TC) and supplemental type
certificate (STC)) holders to substantiate
that their fuel tank systems can prevent
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ignition sources in the fuel tanks. This
requirement applies to type design
holders for large turbine-powered
transport airplanes and for subsequent
modifications to those airplanes. It
requires them to perform design reviews
and to develop design changes and
maintenance procedures if their designs
do not meet the new fuel tank safety
standards. As explained in the preamble
to the rule, we intended to adopt
airworthiness directives to mandate any
changes found necessary to address
unsafe conditions identified as a result
of these reviews.
In evaluating these design reviews, we
have established four criteria intended
to define the unsafe conditions
associated with fuel tank systems that
require corrective actions. The
percentage of operating time during
which fuel tanks are exposed to
flammable conditions is one of these
criteria. The other three criteria address
the failure types under evaluation:
single failures, single failures in
combination with another latent
condition(s), and in-service failure
experience. For all four criteria, the
evaluations included consideration of
previous actions taken that may mitigate
the need for further action.
We have determined that the actions
identified in this AD are necessary to
reduce the potential of ignition sources
inside fuel tanks, which, in combination
with flammable fuel vapors, could result
in fuel tank explosions and consequent
loss of the airplane.
Relevant Rulemaking
On December 23, 2002, we issued AD
2002–24–52, amendment 39–12993 (68
6405
FR 14, January 2, 2003), for all Boeing
Model 747–400, –400D, and –400F
series airplanes. That AD requires
revising the airplane flight manual
(AFM) to require the flightcrew to
maintain certain minimum fuel levels in
the center fuel tanks, and to prohibit the
use of the horizontal stabilizer fuel tank.
That AD resulted from reports
indicating that two fuel pumps showed
evidence of extreme localized
overheating of parts in the priming and
vapor pump section of the fuel pump.
We issued that AD to require the
flightcrew to maintain certain minimum
fuel levels in the center fuel tanks, and
to prohibit the use of the horizontal
stabilizer fuel tank.
Other Relevant Rulemaking
We also issued the following ADs:
OTHER RELEVANT RULEMAKING
AD—
Requires—
And—
And—
2001–12–21,
amendment
39–
12277 (66 FR 33170, June 21,
2001).
Revising the AFM to include procedures to prevent dry operation of the center wing fuel
tank override/jettison pumps.
For certain airplanes, revising the
AFM.
For certain airplanes, prohibits operation of the horizontal stabilizer tank transfer pumps in
flight.
For all airplanes, performing repetitive inspections for wear or
damage of the inlet check
valves and inlet adapters of the
override/jettison pumps, and
doing corrective actions if necessary.
Prohibits installation of any
uninspected pumps.
For certain airplanes, requires installing improved fuel pumps,
which terminates the AFM revision.
Reworking of certain components,
which ends the repetitive inspection requirements.
2001–21–07,
amendment
39–
12478 (66 FR 54652, October
30, 2001).
2002–19–52,
amendment
12900 (67 FR 61253,
tember 30, 2002).
39–
Sep-
Removing currently required AFM
revisions, inserting new AFM
revisions, and installing placards to alert the flightcrew to
the operating restrictions.
Actions Since Existing ADs Were Issued
The preambles to ADs 2002–24–52
and 2002–19–52 explain that we
consider the requirements ‘‘interim
action’’ and were considering further
rulemaking. We now have determined
that further rulemaking is indeed
Permits the AFM revision and
placard to be removed under
certain conditions.
necessary, and this proposed AD
follows from that determination.
We have reviewed the following
service bulletins:
SERVICE BULLETINS
Boeing Alert Service Bulletin—
For Model—
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747–31A2350, Revision 1, dated March 17, 2005 ...................................
747–31A2351, Revision 1, dated March 17, 2005 ...................................
747–31A2352, Revision 1, dated March 17, 2005 ...................................
The service bulletins describe
procedures for installing new integrated
display software in the integrated
display units (IDUs) and electronic
flight instrument system (EFIS)/engine
indication and crew alerting system
(EICAS) interface units (EIU) of the
flight deck. The new software provides
new IDS EICAS fuel system messages.
These messages alert the flightcrew
when to shut the fuel pumps off.
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747–400 and 747–400F series airplanes.
747–400, 747–400D, and 747–400F series airplanes.
747–400 and 747–400F series airplanes.
Accomplishing the actions specified in
the service information is intended to
adequately address the unsafe
condition.
Each service bulletin described
previously refers to Rockwell Collins
Service Bulletins IDS–7000–31–49, IDS–
7000–31–50, or IDS–7000–31–51; all
dated June 28, 2004; as applicable; as an
additional source of service information
for installing the new software.
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FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to develop on
other airplanes of the same type design.
For this reason, we are proposing this
AD, which would supersede AD 2002–
24–52 to continue to require revising the
AFM to require the flightcrew to
maintain certain minimum fuel levels in
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the center fuel tanks, and to prohibit the
use of the horizontal stabilizer fuel tank.
The proposed AD also would require:
• Accomplishing the actions
specified in the Boeing service
information described previously;
• Revising the Limitations section of
the AFM to include procedures to
prevent dry operation of the center wing
and horizontal stabilizer fuel tanks; for
maintaining minimum fuel levels; and
for de-fueling fuel tanks; and
• For certain airplanes: Removing
G13 pin ground wires of the wire
integration unit on the E2–6 electronic
shelf of the left, center, and right
electronics interface units at certain
connector locations.
After installing the new software and
incorporating the new AFM revisions,
the AFM revision required by AD 2002–
24–52 and certain AFM revisions
required by ADs 2001–12–21, 2001–21–
07, and 2002–19–52 may be removed.
Change to Existing AD
This proposed AD would retain all
the requirements of AD 2002–24–52.
Since AD 2002–24–52 was issued, the
AD format has been revised, and certain
paragraphs have been rearranged. As a
result, the corresponding paragraph
identifiers have changed in this
proposed AD, as listed in the following
table:
REVISED PARAGRAPH IDENTIFIERS
Corresponding requirement in this proposed AD
Requirement in AD
2002–24–52
paragraph (a) ............
paragraph (b) ............
paragraph (g).
paragraph (h).
Costs of Compliance
There are about 520 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Action
Average labor rate
per hour
Work hours
Parts
Cost per airplane
Number of U.S.registered airplanes
Fleet cost
AFM revision (required by AD 2002–
24–52).
Installation of new IDS
software (new proposed action).
Removal of G–13 pin
ground wires (new
proposed action).
1
$65
None .........
$65
101
$6,565.
3
65
$100 .........
295
101
$29,795.
1
65
None .........
65
0
AFM revision (new
proposed action).
1
65
None .........
65
101
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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
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
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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 the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. 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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
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$65 if an affected airplane is imported
and placed on the
U.S. Register in the
future.
$6,565.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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 Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–12993 (68
FR 14, January 2, 2003) and adding the
following new airworthiness directive
(AD):
Boeing: Docket No. FAA–2006–23803;
Directorate Identifier 2005–NM–238–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by March 27, 2006.
Affected ADs
(b) This AD supersedes AD 2002–24–52. In
addition, after accomplishing the
requirements of paragraphs (h) and (k) of this
AD, the airplane flight manual (AFM)
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requirements specified in table 1 of this AD
may be removed.
TABLE 1.—AFFECTED ADS
AFM requirements of—
(1)
(2)
(3)
(4)
Of—
Paragraph (a) ......................................................................................
Paragraph (a) ......................................................................................
Paragraph (c) ......................................................................................
Paragraphs (f) and (g) ........................................................................
AD 2001–12–21, amendment 39–12277.
AD 2001–21–07, amendment 39–12478.
AD 2002–19–52, amendment 39–12900.
This AD.
Applicability
(c) This AD applies to airplanes identified
in table 2 of this AD, certificated in any
category.
TABLE 2.—APPLICABILITY
Boeing model—
As identified in Boeing Service Bulletin—
(1) 747–400, 747–400D, and 747–400F series airplanes .......................
(2) 747–400 and 747–400F series airplanes ...........................................
(3) 747–400 and 747–400F series airplanes ...........................................
Unsafe Condition
(d) This AD results from fuel system
reviews conducted by the manufacturer. We
are issuing this AD to reduce the potential for
ignition sources inside fuel tanks, which, in
combination with flammable fuel vapors,
could result in fuel tank explosions and
consequent loss of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2002–
24–52
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Airplane Flight Manual (AFM) Revision
(f) Within 4 days after receipt of emergency
AD 2002–24–51, instead of complying with
the requirements of paragraph (d) of AD
2002–24–51, revise the Limitations section of
the AFM to include the following (this may
be accomplished by inserting a copy of this
AD into the AFM):
CERTIFICATE LIMITATIONS
Fueling and use of the horizontal stabilizer
tank (if installed) is prohibited.
The center wing tank (CWT) must contain
a minimum of 17,000 pounds (7,700
kilograms) prior to engine start, if the CWT
override/jettison pumps are to be selected
ON during flight.
The CWT fuel quantity indication system
must be operative to dispatch with CWT
mission fuel.
Both CWT override/jettison pump switches
must be selected OFF at or before CWT fuel
747–31A2351, Revision 1, dated March 17, 2005.
747–31A2350, Revision 1, dated March 17, 2005.
747–31A2352, Revision 1, dated March 17, 2005.
quantity reaches 7,000 pounds (3,200
kilograms), if CWT fuel quantity is less than
50,000 pounds (22,700 kilograms) prior to
engine start. The CWT override pumps may
be selected ON during stabilized cruise
conditions. Both CWT override/jettison
pump switches must be selected OFF at or
before the CWT fuel quantity reaches 3,000
pounds (1,400 kilograms).
Note: With CWT override/jettison pumps
selected OFF and CWT fuel quantity greater
than 6,000 pounds (2,800 kilograms), the
FUEL OVRD CTR L & R EICAS messages will
be displayed. Do not accomplish the
associated non-normal procedure.
Both CWT override/jettison pump switches
must be selected OFF at or before CWT fuel
quantity reaches 3,000 pounds (1,400
kilograms), if CWT fuel quantity is greater
than or equal to 50,000 pounds (22,700
kilograms) prior to engine start.
Both CWT override/jettison pumps must be
selected OFF when either CWT override/
jettison fuel pump low pressure light
illuminates.
Warning: Do not reset a tripped fuel pump
circuit breaker.
Warning: Do not cycle CWT override/
jettison pump switches from ON to OFF to
ON with any continuous low pressure
indication present.
Note: The center wing tank may be
emptied normally during an emergency fuel
jettison.
Note: In a low fuel situation, both CWT
override/jettison pumps may be selected ON
and all CWT fuel may be used.
If a center wing tank pump fails with fuel
in the center tank, accomplish the FUEL
OVRD CTR L, R non-normal procedure.
If the main tanks are not full, the zero fuel
gross weight of the airplane plus the weight
of CWT tank fuel may exceed the maximum
zero fuel gross weight by up to 7,000 pounds
(3,200 kilograms) for takeoff, climb, cruise,
descent, and landing, provided that the
effects of balance (CG) have been considered.
When defueling any fuel tanks, the Fuel
Pump Low Pressure indication lights must be
monitored and the fuel pumps positioned to
OFF at the first indication of fuel pump low
pressure. Defueling with passengers on board
is prohibited.
The limitations contained in this AD
supersede any conflicting basic airplane
flight manual limitations.’’
(g) If an operator has already complied
with AD 2002–24–51, it can comply with
paragraph (f) of this AD by deleting the
phrase ‘‘if a placard prohibiting its use is
installed’’ from the first paragraph of the
AFM revision required by paragraph (d) of
AD 2002–24–51.
New Actions Required by This AD
Installation of New Integrated Display
System (IDS) Software
(h) Within 6 months after the effective date
of this AD, install new IDS software in the
integrated display units and electronic flight
instrument system/engine indication and
crew alerting system interface units of the
flight deck, in accordance with the
Accomplishment Instructions of the
applicable service bulletin in table 3 of this
AD.
TABLE 3.—REVISION 1 OF SERVICE BULLETINS
For model—
Boeing service bulletin—
(1) 747–400, 747–400D, and 747–400F series airplanes .......................
(2) 747–400 and 747–400F series airplanes ...........................................
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747–31A2351, Revision 1, dated March 17, 2005.
747–31A2350, Revision 1, dated March 17, 2005.
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TABLE 3.—REVISION 1 OF SERVICE BULLETINS—Continued
For model—
Boeing service bulletin—
(3) 747–400 and 747–400F series airplanes ...........................................
Note 1: Each service bulletin identified in
table 3 of this AD refers to Rockwell Collins
Service Bulletins IDS–7000–31–49, IDS–
7000–31–50, or IDS–7000–31–51; all dated
June 28, 2004; as applicable; as an additional
747–31A2352, Revision 1, dated March 17, 2005.
source of service information for installing
the new IDS software.
(i) Installing new IDS software before the
effective date of this AD in accordance with
the applicable service bulletin in table 4 of
this AD, is acceptable for compliance with
the requirements of paragraph (h) of this AD.
TABLE 4.—ORIGINAL SERVICE BULLETINS
For model—
Boeing service bulletin—
(1) 747–400, 747–400D, and 747–400F series airplanes .......................
(2) 747–400 and 747–400F series airplanes ...........................................
(3) 747–400 and 747–400F series airplanes ...........................................
Removal of Pin Ground Wires
(j) For airplanes on which FR–HiTEMP fuel
pumps have been incorporated in accordance
with Boeing Service Bulletin 747–28–2258,
dated December 19, 2003; or Revision 1,
dated August 11, 2005: Before further flight
after installing the new IDS software required
by paragraph (h) of this AD, remove the G13
pin ground wires of the wire integration unit
on the E2–6 electronic shelf of the left,
center, and right electronics interface units,
that correspond to the connector locations in
table 5 of this AD, in accordance with a
method approved by the Manager, Seattle
Aircraft Certification Office (ACO), FAA.
Chapter 20–41–03 of the Boeing 747–400
Aircraft Maintenance Manual is one
approved method.
TABLE 5.—CONNECTOR LOCATION
Connector
DM7353CA ................
DM7352CA ................
DM7351CA ................
Location
Left EIU.
Center EIU.
Right EIU.
AFM Revision
(k) Concurrently with the requirements of
paragraph (h) of this AD, revise the
Limitations section of the AFM to include the
following (this may be done by inserting a
copy of this AD into the AFM):
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Certification Limitations
Center Wing Tank (CWT): The CWT fuel
quantity indication system must be operative
to dispatch with CWT mission fuel.
The CWT must contain a minimum of
17,000 pounds (7,700 kilograms) prior to
engine start, if the CWT override/jettison
pumps are to be selected ON during takeoff.
If the FUEL LOW CTR L or R message is
displayed both CWT override/jettison pumps
must be selected OFF.
If the FUEL PRESS CTR L or R message is
displayed, the corresponding CWT override/
jettison pump must be selected OFF.
Horizontal Stabilizer Tank (HST): The
following additional limitations must be
followed if the HST is fueled and used:
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747–31A2351, dated September 3, 2004.
747–31A2350, dated September 3, 2004.
747–31A2352, dated September 3, 2004.
The HST fuel quantity indication system
must be operative to dispatch with HST
mission fuel.
If the FUEL PMP STB L or R message is
displayed while on the ground both HST
pumps must be selected OFF.
If the FUEL LOW STAB L or R message is
displayed in flight the corresponding HST
pump must be selected OFF.
If the FUEL PRESS STAB L or R is
displayed the corresponding HST pump must
be selected OFF.
The remaining fuel in the HST must be
considered unusable, and the effects of that
unusable fuel on balance (CG) must be
considered.
Warning: Do not reset a tripped fuel pump
circuit breaker.
Defueling: Prior to defueling any fuel tanks,
perform a lamp test of the respective Fuel
Pump Low Pressure indication lights. When
defueling, the Fuel Pump Low Pressure
indication lights must be monitored and the
fuel pumps positioned to OFF at the first
indication of fuel pump low pressure. When
defueling with passengers on board, fuel
pump switches must be selected OFF at or
above approximately 7,000 pounds (3,200
kilograms) for the CWT, 3,000 pounds (1,400
kilograms) for main tanks, and 2,100 pounds
(1,000 kilograms) for the HST.
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Issued in Renton, Washington, on January
30, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–1682 Filed 2–7–06; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23820; Directorate
Identifier 2005–NM–249–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–102, –103, and –106
Airplanes; and Model DHC–8–200 and
–300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to revise
an existing airworthiness directive (AD)
that applies to certain Bombardier
Model DHC–8–102, –103, and –106
airplanes; and Model DHC–8–200 and
–300 series airplanes. The existing AD
currently requires performing a onetime inspection to detect chafing of
electrical wires in the cable trough
below the cabin floor; repairing, if
necessary; installing additional tiemounts and tie-wraps; applying sealant
to rivet heads; and modifying electrical
wires in certain sections. This proposed
AD would, for certain airplanes,
eliminate the requirement to modify
electrical wires in certain sections. This
proposed AD results from a report
indicating that the modification of
electrical wires does not need to be
done on certain airplanes subject to the
existing AD. We are proposing this AD
to prevent chafing of electrical wires,
which could result in an uncommanded
shutdown of an engine during flight.
DATES: We must receive comments on
this proposed AD by March 10, 2006.
E:\FR\FM\08FEP1.SGM
08FEP1
]]>Agencies
[Federal Register Volume 71, Number 26 (Wednesday, February 8, 2006)]
[Proposed Rules]
[Pages 6404-6408]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-1682]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23803; Directorate Identifier 2005-NM-238-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-400, 747-400D, and
747-400F Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking.
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to all Boeing Model 747-400, -400D, and -
400F series airplanes. The existing AD currently requires revising the
airplane flight manual (AFM) to require the flightcrew to maintain
certain minimum fuel levels in the center fuel tanks, and to prohibit
the use of the horizontal stabilizer fuel tank. This proposed AD would
require installing new integrated display software in the integrated
display units and electronic flight instrument system/engine indication
and crew alerting system interface units (EIUs) of the flight deck.
This proposed AD also would require revising the AFM to include
procedures to prevent dry operation of the center wing and horizontal
stabilizer fuel tanks; for maintaining minimum fuel levels; and for de-
fueling fuel tanks. For certain airplanes, the proposed AD also
requires removing G13 pin ground wires of a certain wire integration
unit of the EIUs at certain connector locations. This proposed AD
results from fuel system reviews conducted by the manufacturer. We are
proposing this AD to reduce the potential for ignition sources inside
fuel tanks, which, in combination with flammable fuel vapors, could
result in fuel tank explosions and consequent loss of the airplane.
DATES: We must receive comments on this proposed AD by March 27, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT: Sulmo Mariano, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone
(425) 917-6501; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2006-23803; Directorate Identifier 2005-NM-238-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
proposed AD. We will consider all comments received by the closing date
and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or may
visit https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
The FAA has examined the underlying safety issues involved in fuel
tank explosions on several large transport airplanes, including the
adequacy of existing regulations, the service history of airplanes
subject to those regulations, and existing maintenance practices for
fuel tank systems. As a result of those findings, we issued a
regulation titled ``Transport Airplane Fuel Tank System Design Review,
Flammability Reduction and Maintenance and Inspection Requirements''
(67 FR 23086, May 7, 2001). In addition to new airworthiness standards
for transport airplanes and new maintenance requirements, this rule
included Special Federal Aviation Regulation No. 88 (``SFAR 88,''
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
Among other actions, SFAR 88 requires certain type design (i.e.,
type certificate (TC) and supplemental type certificate (STC)) holders
to substantiate that their fuel tank systems can prevent
[[Page 6405]]
ignition sources in the fuel tanks. This requirement applies to type
design holders for large turbine-powered transport airplanes and for
subsequent modifications to those airplanes. It requires them to
perform design reviews and to develop design changes and maintenance
procedures if their designs do not meet the new fuel tank safety
standards. As explained in the preamble to the rule, we intended to
adopt airworthiness directives to mandate any changes found necessary
to address unsafe conditions identified as a result of these reviews.
In evaluating these design reviews, we have established four
criteria intended to define the unsafe conditions associated with fuel
tank systems that require corrective actions. The percentage of
operating time during which fuel tanks are exposed to flammable
conditions is one of these criteria. The other three criteria address
the failure types under evaluation: single failures, single failures in
combination with another latent condition(s), and in-service failure
experience. For all four criteria, the evaluations included
consideration of previous actions taken that may mitigate the need for
further action.
We have determined that the actions identified in this AD are
necessary to reduce the potential of ignition sources inside fuel
tanks, which, in combination with flammable fuel vapors, could result
in fuel tank explosions and consequent loss of the airplane.
Relevant Rulemaking
On December 23, 2002, we issued AD 2002-24-52, amendment 39-12993
(68 FR 14, January 2, 2003), for all Boeing Model 747-400, -400D, and -
400F series airplanes. That AD requires revising the airplane flight
manual (AFM) to require the flightcrew to maintain certain minimum fuel
levels in the center fuel tanks, and to prohibit the use of the
horizontal stabilizer fuel tank. That AD resulted from reports
indicating that two fuel pumps showed evidence of extreme localized
overheating of parts in the priming and vapor pump section of the fuel
pump. We issued that AD to require the flightcrew to maintain certain
minimum fuel levels in the center fuel tanks, and to prohibit the use
of the horizontal stabilizer fuel tank.
Other Relevant Rulemaking
We also issued the following ADs:
Other Relevant Rulemaking
----------------------------------------------------------------------------------------------------------------
AD-- Requires-- And-- And--
----------------------------------------------------------------------------------------------------------------
2001-12-21, amendment 39-12277 (66 FR Revising the AFM to For certain airplanes, For certain airplanes,
33170, June 21, 2001). include procedures to prohibits operation of requires installing
prevent dry operation the horizontal improved fuel pumps,
of the center wing stabilizer tank which terminates the
fuel tank override/ transfer pumps in AFM revision.
jettison pumps. flight.
2001-21-07, amendment 39-12478 (66 FR For certain airplanes, For all airplanes, Reworking of certain
54652, October 30, 2001). revising the AFM. performing repetitive components, which ends
inspections for wear the repetitive
or damage of the inlet inspection
check valves and inlet requirements.
adapters of the
override/jettison
pumps, and doing
corrective actions if
necessary.
2002-19-52, amendment 39-12900 (67 FR Removing currently Prohibits installation Permits the AFM
61253, September 30, 2002). required AFM of any uninspected revision and placard
revisions, inserting pumps. to be removed under
new AFM revisions, and certain conditions.
installing placards to
alert the flightcrew
to the operating
restrictions.
----------------------------------------------------------------------------------------------------------------
Actions Since Existing ADs Were Issued
The preambles to ADs 2002-24-52 and 2002-19-52 explain that we
consider the requirements ``interim action'' and were considering
further rulemaking. We now have determined that further rulemaking is
indeed necessary, and this proposed AD follows from that determination.
We have reviewed the following service bulletins:
Service Bulletins
------------------------------------------------------------------------
Boeing Alert Service Bulletin-- For Model--
------------------------------------------------------------------------
747-31A2350, Revision 1, dated March 747-400 and 747-400F series
17, 2005. airplanes.
747-31A2351, Revision 1, dated March 747-400, 747-400D, and 747-400F
17, 2005. series airplanes.
747-31A2352, Revision 1, dated March 747-400 and 747-400F series
17, 2005. airplanes.
------------------------------------------------------------------------
The service bulletins describe procedures for installing new
integrated display software in the integrated display units (IDUs) and
electronic flight instrument system (EFIS)/engine indication and crew
alerting system (EICAS) interface units (EIU) of the flight deck. The
new software provides new IDS EICAS fuel system messages. These
messages alert the flightcrew when to shut the fuel pumps off.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
Each service bulletin described previously refers to Rockwell
Collins Service Bulletins IDS-7000-31-49, IDS-7000-31-50, or IDS-7000-
31-51; all dated June 28, 2004; as applicable; as an additional source
of service information for installing the new software.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to develop on other airplanes of the
same type design. For this reason, we are proposing this AD, which
would supersede AD 2002-24-52 to continue to require revising the AFM
to require the flightcrew to maintain certain minimum fuel levels in
[[Page 6406]]
the center fuel tanks, and to prohibit the use of the horizontal
stabilizer fuel tank. The proposed AD also would require:
Accomplishing the actions specified in the Boeing service
information described previously;
Revising the Limitations section of the AFM to include
procedures to prevent dry operation of the center wing and horizontal
stabilizer fuel tanks; for maintaining minimum fuel levels; and for de-
fueling fuel tanks; and
For certain airplanes: Removing G13 pin ground wires of
the wire integration unit on the E2-6 electronic shelf of the left,
center, and right electronics interface units at certain connector
locations.
After installing the new software and incorporating the new AFM
revisions, the AFM revision required by AD 2002-24-52 and certain AFM
revisions required by ADs 2001-12-21, 2001-21-07, and 2002-19-52 may be
removed.
Change to Existing AD
This proposed AD would retain all the requirements of AD 2002-24-
52. Since AD 2002-24-52 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in
Requirement in AD 2002-24-52 this proposed AD
------------------------------------------------------------------------
paragraph (a)............................. paragraph (g).
paragraph (b)............................. paragraph (h).
------------------------------------------------------------------------
Costs of Compliance
There are about 520 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Parts Cost per airplane registered Fleet cost
rate per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
AFM revision (required by AD 2002- 1 $65 None............... $65 101 $6,565.
24-52).
Installation of new IDS software 3 65 $100............... 295 101 $29,795.
(new proposed action).
Removal of G-13 pin ground wires 1 65 None............... 65 0 $65 if an affected
(new proposed action). airplane is
imported and placed
on the U.S.
Register in the
future.
AFM revision (new proposed 1 65 None............... 65 101 $6,565.
action).
--------------------------------------------------------------------------------------------------------------------------------------------------------
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
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-12993 (68 FR 14, January 2, 2003) and adding the
following new airworthiness directive (AD):
Boeing: Docket No. FAA-2006-23803; Directorate Identifier 2005-NM-
238-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by March 27,
2006.
Affected ADs
(b) This AD supersedes AD 2002-24-52. In addition, after
accomplishing the requirements of paragraphs (h) and (k) of this AD,
the airplane flight manual (AFM)
[[Page 6407]]
requirements specified in table 1 of this AD may be removed.
Table 1.--Affected ADs
------------------------------------------------------------------------
AFM requirements of-- Of--
------------------------------------------------------------------------
(1) Paragraph (a)...................... AD 2001-12-21, amendment 39-
12277.
(2) Paragraph (a)...................... AD 2001-21-07, amendment 39-
12478.
(3) Paragraph (c)...................... AD 2002-19-52, amendment 39-
12900.
(4) Paragraphs (f) and (g)............. This AD.
------------------------------------------------------------------------
Applicability
(c) This AD applies to airplanes identified in table 2 of this
AD, certificated in any category.
Table 2.--Applicability
------------------------------------------------------------------------
As identified in Boeing Service
Boeing model-- Bulletin--
------------------------------------------------------------------------
(1) 747-400, 747-400D, and 747-400F 747-31A2351, Revision 1, dated
series airplanes. March 17, 2005.
(2) 747-400 and 747-400F series 747-31A2350, Revision 1, dated
airplanes. March 17, 2005.
(3) 747-400 and 747-400F series 747-31A2352, Revision 1, dated
airplanes. March 17, 2005.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from fuel system reviews conducted by the
manufacturer. We are issuing this AD to reduce the potential for
ignition sources inside fuel tanks, which, in combination with
flammable fuel vapors, could result in fuel tank explosions and
consequent loss of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2002-24-52
Airplane Flight Manual (AFM) Revision
(f) Within 4 days after receipt of emergency AD 2002-24-51,
instead of complying with the requirements of paragraph (d) of AD
2002-24-51, revise the Limitations section of the AFM to include the
following (this may be accomplished by inserting a copy of this AD
into the AFM):
CERTIFICATE LIMITATIONS
Fueling and use of the horizontal stabilizer tank (if installed)
is prohibited.
The center wing tank (CWT) must contain a minimum of 17,000
pounds (7,700 kilograms) prior to engine start, if the CWT override/
jettison pumps are to be selected ON during flight.
The CWT fuel quantity indication system must be operative to
dispatch with CWT mission fuel.
Both CWT override/jettison pump switches must be selected OFF at
or before CWT fuel quantity reaches 7,000 pounds (3,200 kilograms),
if CWT fuel quantity is less than 50,000 pounds (22,700 kilograms)
prior to engine start. The CWT override pumps may be selected ON
during stabilized cruise conditions. Both CWT override/jettison pump
switches must be selected OFF at or before the CWT fuel quantity
reaches 3,000 pounds (1,400 kilograms).
Note: With CWT override/jettison pumps selected OFF and CWT fuel
quantity greater than 6,000 pounds (2,800 kilograms), the FUEL OVRD
CTR L & R EICAS messages will be displayed. Do not accomplish the
associated non-normal procedure.
Both CWT override/jettison pump switches must be selected OFF at
or before CWT fuel quantity reaches 3,000 pounds (1,400 kilograms),
if CWT fuel quantity is greater than or equal to 50,000 pounds
(22,700 kilograms) prior to engine start.
Both CWT override/jettison pumps must be selected OFF when
either CWT override/jettison fuel pump low pressure light
illuminates.
Warning: Do not reset a tripped fuel pump circuit breaker.
Warning: Do not cycle CWT override/jettison pump switches from
ON to OFF to ON with any continuous low pressure indication present.
Note: The center wing tank may be emptied normally during an
emergency fuel jettison.
Note: In a low fuel situation, both CWT override/jettison pumps
may be selected ON and all CWT fuel may be used.
If a center wing tank pump fails with fuel in the center tank,
accomplish the FUEL OVRD CTR L, R non-normal procedure.
If the main tanks are not full, the zero fuel gross weight of
the airplane plus the weight of CWT tank fuel may exceed the maximum
zero fuel gross weight by up to 7,000 pounds (3,200 kilograms) for
takeoff, climb, cruise, descent, and landing, provided that the
effects of balance (CG) have been considered.
When defueling any fuel tanks, the Fuel Pump Low Pressure
indication lights must be monitored and the fuel pumps positioned to
OFF at the first indication of fuel pump low pressure. Defueling
with passengers on board is prohibited.
The limitations contained in this AD supersede any conflicting
basic airplane flight manual limitations.''
(g) If an operator has already complied with AD 2002-24-51, it
can comply with paragraph (f) of this AD by deleting the phrase ``if
a placard prohibiting its use is installed'' from the first
paragraph of the AFM revision required by paragraph (d) of AD 2002-
24-51.
New Actions Required by This AD
Installation of New Integrated Display System (IDS) Software
(h) Within 6 months after the effective date of this AD, install
new IDS software in the integrated display units and electronic
flight instrument system/engine indication and crew alerting system
interface units of the flight deck, in accordance with the
Accomplishment Instructions of the applicable service bulletin in
table 3 of this AD.
Table 3.--Revision 1 of Service Bulletins
------------------------------------------------------------------------
For model-- Boeing service bulletin--
------------------------------------------------------------------------
(1) 747-400, 747-400D, and 747-400F 747-31A2351, Revision 1, dated
series airplanes. March 17, 2005.
(2) 747-400 and 747-400F series 747-31A2350, Revision 1, dated
airplanes. March 17, 2005.
[[Page 6408]]
(3) 747-400 and 747-400F series 747-31A2352, Revision 1, dated
airplanes. March 17, 2005.
------------------------------------------------------------------------
Note 1: Each service bulletin identified in table 3 of this AD
refers to Rockwell Collins Service Bulletins IDS-7000-31-49, IDS-
7000-31-50, or IDS-7000-31-51; all dated June 28, 2004; as
applicable; as an additional source of service information for
installing the new IDS software.
(i) Installing new IDS software before the effective date of
this AD in accordance with the applicable service bulletin in table
4 of this AD, is acceptable for compliance with the requirements of
paragraph (h) of this AD.
Table 4.--Original Service Bulletins
------------------------------------------------------------------------
For model-- Boeing service bulletin--
------------------------------------------------------------------------
(1) 747-400, 747-400D, and 747-400F 747-31A2351, dated September 3,
series airplanes. 2004.
(2) 747-400 and 747-400F series 747-31A2350, dated September 3,
airplanes. 2004.
(3) 747-400 and 747-400F series 747-31A2352, dated September 3,
airplanes. 2004.
------------------------------------------------------------------------
Removal of Pin Ground Wires
(j) For airplanes on which FR-HiTEMP fuel pumps have been
incorporated in accordance with Boeing Service Bulletin 747-28-2258,
dated December 19, 2003; or Revision 1, dated August 11, 2005:
Before further flight after installing the new IDS software required
by paragraph (h) of this AD, remove the G13 pin ground wires of the
wire integration unit on the E2-6 electronic shelf of the left,
center, and right electronics interface units, that correspond to
the connector locations in table 5 of this AD, in accordance with a
method approved by the Manager, Seattle Aircraft Certification
Office (ACO), FAA. Chapter 20-41-03 of the Boeing 747-400 Aircraft
Maintenance Manual is one approved method.
Table 5.--Connector Location
------------------------------------------------------------------------
Connector Location
------------------------------------------------------------------------
DM7353CA.................................. Left EIU.
DM7352CA.................................. Center EIU.
DM7351CA.................................. Right EIU.
------------------------------------------------------------------------
AFM Revision
(k) Concurrently with the requirements of paragraph (h) of this
AD, revise the Limitations section of the AFM to include the
following (this may be done by inserting a copy of this AD into the
AFM):
Certification Limitations
Center Wing Tank (CWT): The CWT fuel quantity indication system
must be operative to dispatch with CWT mission fuel.
The CWT must contain a minimum of 17,000 pounds (7,700
kilograms) prior to engine start, if the CWT override/jettison pumps
are to be selected ON during takeoff.
If the FUEL LOW CTR L or R message is displayed both CWT
override/jettison pumps must be selected OFF.
If the FUEL PRESS CTR L or R message is displayed, the
corresponding CWT override/jettison pump must be selected OFF.
Horizontal Stabilizer Tank (HST): The following additional
limitations must be followed if the HST is fueled and used:
The HST fuel quantity indication system must be operative to
dispatch with HST mission fuel.
If the FUEL PMP STB L or R message is displayed while on the
ground both HST pumps must be selected OFF.
If the FUEL LOW STAB L or R message is displayed in flight the
corresponding HST pump must be selected OFF.
If the FUEL PRESS STAB L or R is displayed the corresponding HST
pump must be selected OFF.
The remaining fuel in the HST must be considered unusable, and
the effects of that unusable fuel on balance (CG) must be
considered.
Warning: Do not reset a tripped fuel pump circuit breaker.
Defueling: Prior to defueling any fuel tanks, perform a lamp
test of the respective Fuel Pump Low Pressure indication lights.
When defueling, the Fuel Pump Low Pressure indication lights must be
monitored and the fuel pumps positioned to OFF at the first
indication of fuel pump low pressure. When defueling with passengers
on board, fuel pump switches must be selected OFF at or above
approximately 7,000 pounds (3,200 kilograms) for the CWT, 3,000
pounds (1,400 kilograms) for main tanks, and 2,100 pounds (1,000
kilograms) for the HST.
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, Seattle ACO, FAA, has the authority to
approve AMOCs for this AD, if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Issued in Renton, Washington, on January 30, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-1682 Filed 2-7-06; 8:45 am]
BILLING CODE 4910-13-P
