Airworthiness Directives; Boeing Model 747-400, 747-400D, and 747-400F Series Airplanes, 26317-26322 [E9-12742]
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FAA AD Differences
DEPARTMENT OF TRANSPORTATION
Note 1: This AD differs from the MCAI
and/or service information as follows:
Although the MCAI or service information
allows further flight after cracks are found
during compliance with the required action,
paragraph (f)(2) of this AD requires that you
replace any cracked lug of the RAT machined
support with a new support before further
flight.
Federal Aviation Administration
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Kenny Kaulia,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–2848; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
ˆ
(h) Refer to MCAI Agencia Nacional de
Aviacao Civil (ANAC) Airworthiness
¸˜
Directives 2008–10–05 and 2008–10–06, both
dated November 10, 2008; Embraer Service
Bulletin 170–53–0057, dated February 21,
2008; and Embraer Service Bulletin 190–53–
0027, dated February 18, 2008; for related
information.
Issued in Renton, Washington, on May 20,
2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–12802 Filed 6–1–09; 8:45 am]
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14 CFR Part 39
[Docket No. FAA–2009–0454; Directorate
Identifier 2008–NM–156–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–400, 747–400D, and 747–
400F Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
Boeing Model 747–400, 747–400D, and
747–400F series airplanes. For all
airplanes, this proposed AD would
require installing new pump control and
time delay relays, doing related
investigative and corrective actions if
necessary, and changing the wiring for
the center and main fuel tanks override/
jettison fuel pumps; and, for certain
airplanes, installing new relays and
wiring for the horizontal stabilizer
override/jettison fuel pumps. This
proposed AD would also require a
revision to the maintenance program to
incorporate Airworthiness Limitation
No. 28–AWL–24 and No. 28–AWL–26.
For certain airplanes, this proposed AD
would also require installing an
automatic shutoff system for the
horizontal stabilizer tank fuel pumps
and installing a new integrated display
system. This proposed AD results from
fuel system reviews conducted by the
manufacturer. We are proposing this AD
to prevent uncommanded operation of
certain override/jettison pumps which
could cause overheat, electrical arcs, or
frictional sparks, and could lead to an
ignition source inside a fuel tank. This
condition, in combination with
flammable fuel vapors, could result in a
fuel tank explosion and consequent loss
of the airplane.
DATES: We must receive comments on
this proposed AD by July 17, 2009.
ADDRESSES: You may send comments 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–
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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.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207;
telephone 206–544–5000, extension 1,
fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Jon
Regimbal, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6506; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2009–0454; Directorate Identifier
2008–NM–156–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed 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 proposed AD.
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
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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’’ (66 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
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 a 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.
Safety assessments conducted by
Boeing indicate that there is a risk of an
ignition source in the main and center
fuel tanks for Model 747–400, 747–
400D, and 747–400F series airplanes,
and in the horizontal stabilizer fuel
tanks of Model 747–400 series airplanes,
if the override/jettison pump continues
to run for an extended time after the fuel
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level goes below the pump inlet. The
pump is normally commanded off if the
fuel level goes below the pump inlet,
but if a single failure in the pump
control circuitry occurs, a pump can
continue to run after it is commanded
off. Uncommanded operation of certain
override/jettison pumps could cause
overheat, electrical arcs, or frictional
sparks, and could lead to an ignition
source inside a fuel tank. This
condition, in combination with
flammable fuel vapors, could result in a
fuel tank explosion and consequent loss
of the airplane.
Other Related Rulemaking
Installing a new integrated display
system (IDS) in accordance with Boeing
Service Bulletin 747–31–2376, 747–31–
2377, or 747–31–2378, all dated
September 5, 2006, as applicable, would
provide an acceptable substitute for
complying with certain paragraphs of
the ADs listed below.
• Paragraph E. of AD 90–09–06,
amendment 39–6581 (55 FR 15217,
April 23, 1990). That AD applies to all
Model 747 series airplanes and requires,
among other actions, installing a system
to provide visual warning signals to
alert flightcrew members and ground
crew personnel of certain incorrect
indications.
• Paragraph (b) of AD 91–13–10 R1,
amendment 39–8158 (57 FR 2446,
January 22, 1992). That AD applies to
certain Boeing Model 747 and 767 series
airplanes and requires, among other
actions, replacing the engine indicating
and crew alerting system (EICAS)
computers.
• Paragraph (d)(1) of AD 96–07–09,
amendment 39–9558 (61 FR 14608,
April 3, 1996). That AD applies to all
Boeing Model 747–400, 757, and 767
series airplanes and requires, among
other actions, installing an upgraded
EICAS computer that provides
‘‘advisory’’ messages to the flightcrew to
indicate an impending engine fuel filter
bypass condition for each engine.
• Paragraph (a)(3)(iii) of AD 2000–02–
22, amendment 39–11540 (65 FR 5222,
February 3, 2000). That AD applies to
certain Boeing Model 747–400 series
airplanes and requires, among other
actions, modifying the IDS software.
• Paragraph (a)(2)(ii) of AD 2000–12–
21, amendment 39–11799 (65 FR 39079,
June 23, 2000). [A correction of that AD
was published in the Federal Register
on July 18, 2000 (65 FR 44432).] That
AD requires, among other actions,
modifying the IDS software.
• Paragraph (d)(2)(iv) of AD 2003–16–
16, amendment 39–13269 (68 FR 51439,
August 27, 2003). That AD applies to
certain Boeing Model 747–400 series
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airplanes and requires, among other
actions, installing new IDS software in
six integrated display units and three
electronic flight information (EFI)/
EICAS interface units.
• Paragraph (d)(1) of AD 2004–10–05,
amendment 39–13635 (69 FR 28052,
May 18, 2004). That AD applies to
certain Boeing Model 747–400, 747–
400D, 747–400F, 757–200, 757–200PF,
757–200CB, 767–200, 767–300, and
767–300F series airplanes. That AD
requires, among other actions for Model
747–400, –400D, and –400F series
airplanes, replacing the three EFIS/
EICAS interface units (EIU), installing
new software in the integrated display
units (IDUs) and EIUs, replacing certain
central maintenance computers (CMCs),
and installing new software in the
CMCs.
For airplanes with a horizontal
stabilizer fuel tank and with horizontal
stabilizer tank fuel pump auto-shutoff
installed, installing a new IDS in
accordance with Boeing Service Bulletin
747–31–2376, 747–31–2377, or 747–31–
2378, all dated September 5, 2006, as
applicable, would provide an acceptable
method for complying with certain
paragraphs of the ADs listed below,
provided the certificate limitations
enclosed with FAA Letter 140S–06–343,
dated November 17, 2006, are
incorporated into the limitations section
of the applicable airplane flight manual
(AFM) revision specified in the
applicable AD.
• Paragraph (a) of AD 2001–12–21,
amendment 12777 (66 FR 33170, June
21, 2001). That AD applies to all Boeing
Model 747 series airplanes and requires,
among other actions, revising the
Limitations Section of the AFM to
include procedures to prevent dry
operation of the center wing fuel tank
override/jettison pumps and, for certain
airplanes, to prohibit operation of the
horizontal stabilizer tank transfer
pumps in-flight.
• Paragraph (a) of AD 2001–21–07,
amendment 39–12478 (66 FR 54652,
October 30, 2001). That AD applies to
certain Boeing Model 747 series
airplanes and requires, among other
actions, revising the AFM to specify the
amount of fuel necessary for operating
the override/jettison fuel pumps, and to
specify not resetting the circuit breakers
for the override/jettison fuel pumps if
they are tripped.
• Paragraph (c)(2) of AD 2002–19–52,
amendment 39–12900 (67 FR 61253,
September 30, 2002). That AD applies to
all Boeing Model 737–600, –700, –700C,
–800, and –900 series airplanes; Model
747 series airplanes; and Model 757
series airplanes. That AD requires,
among other actions, revising the AFM
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to advise the flightcrew of certain
operating restrictions for maintaining
minimum fuel levels.
• Paragraph (a) of AD 2002–24–52,
amendment 39–12993 (68 FR 14,
January 2, 2003). That AD applies to all
Boeing Model 747–400, –400D, and
–400 F series airplanes and requires,
among other actions, revising the AFM
to require the flightcrew to maintain
certain minimum fuel levels in the
center wing fuel tank, and to prohibit
the use of the horizontal stabilizer fuel
tank.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 747–28A2280, dated
August 7, 2008. This service bulletin
describes procedures for installing new
pump control and time delay relays,
doing related investigative and
corrective actions if necessary, and
changing the wiring for the center and
main fuel tanks override/jettison fuel
pumps. The related investigative and
corrective actions include doing a
general visual inspection for corrosion
of the ground stud assembly during the
installation of the P914 relay panel and
cleaning or replacing the ground stud
assembly if necessary. Boeing Alert
Service Bulletin 747–28A2280 specifies
that the installation of a new integrated
display system (IDS), as described in the
following service bulletins, must be
done before or at the same time as the
actions in the alert service bulletin:
• Boeing Service Bulletin 747–31–
2376, dated September 5, 2006, for
Model 747–400, and –400F series
airplanes that have General Electric
engines, except for airplanes having
variable numbers (V/Ns) RL429, RL430,
RL473, RL511, and RL521, which
received new software in production.
• Boeing Service Bulletin 747–31–
2377, dated September 5, 2006, for
Model 747–400, and –400F series
airplanes that have Pratt & Whitney
engines, except for airplanes having
V/Ns RL456, RL492, and RL502, which
received new software in production.
• Boeing Service Bulletin 747–31–
2378, dated September 5, 2006, for
Model 747–400, –400D, and –400F
series airplanes that have Rolls Royce
engines.
We have also reviewed Boeing Alert
Service Bulletin 747–28A2281, dated
December 13, 2007, for Model 747–400
series airplanes. This service bulletin
describes procedures for installing new
relays and wiring in the horizontal
stabilizer override/jettison fuel pumps.
Boeing Alert Service Bulletin 747–
28A2281 specifies that the installation
of a new automatic shutoff system for
the horizontal stabilizer tank (HST) fuel
pumps, as described in the following
service bulletin, must be done before or
at the same time as the actions in the
alert service bulletin: Boeing Service
Bulletin 747–28A2262, Revision 1,
dated May 8, 2008, for Model 747–400
series airplanes, except for airplanes
having V/Ns RM403, RM441, RM442,
RM443, and RM445.
We have also reviewed Section 9,
‘‘Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements
(CMRs),’’ Boeing 747–400 Maintenance
Planning (MPD) Data Document
D621U400–9, Revision April 2008
(hereafter referred to as ‘‘Document
D621U400–9’’). Sub-section D of
Document D621U400–9 describes AWLs
for fuel tank systems. Sub-section D of
Document D621U400–9 includes the
following fuel system AWLs:
• AWL No. 28–AWL–24, which is a
repetitive functional test to verify
continued functionality of the automatic
shutoff system for the fuel boost pump
of the HST. This AWL applies to Model
747–400 airplanes, line numbers (L/Ns)
1343 and subsequent, and those that
have been modified in accordance with
Boeing Service Bulletin 747–28A2262.
• AWL No. 28–AWL–26, which is a
repetitive operational test to verify the
continued functionality of the
uncommanded on system for the
override/jettison pump of the main 2
and main 3 fuel tanks. This AWL
applies to Model 747–400, –400D, and
–400F airplanes, L/Ns 1380 and
subsequent, and those that have been
modified in accordance with Boeing
Alert Service Bulletin 747–28A2280.
FAA’s Determination and Requirements
of This Proposed AD
We are proposing this AD because we
evaluated all relevant information and
determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design. This proposed AD would
require, for all airplanes installing new
pump control and time delay relays,
doing related investigative and
corrective actions if necessary, and
changing the wiring for the center and
main fuel tanks override/jettison fuel
pumps; and, for certain airplanes,
installing new relays and wiring for the
horizontal stabilizer override/jettison
fuel pumps. This proposed AD would
also require a revision to the
maintenance program to incorporate
Airworthiness Limitation No. 28–AWL–
24 and No. 28–AWL–26. For certain
airplanes, this proposed AD would also
require installing an automatic shutoff
system for the horizontal stabilizer tank
fuel pumps and installing a new
integrated display system.
Costs of Compliance
We estimate that this proposed AD
would affect 102 airplanes of U.S.
registry. The following table provides
the estimated costs for U.S. operators to
comply with this proposed AD. The
average labor rate is $80 per work hour.
ESTIMATED COSTS
Action
Work hours
Parts
Cost per
product
Number of U.S.registered
airplanes
Installing relays/changing wiring for center
and main fuel tanks.
Installing a new IDS and revising the AFM
when done (prior/concurrent action).
Installing relays and wiring for horizontal
stabilizer tank (HST).
Installing a new automatic shutoff for the
HST.
Revising the maintenance program ..........
375 to 394 ........
$95,015 to
$96,971.
Up to $240 .......
102 ...................
2 to 3 ................
$65,015 to
$65,451.
$0 .....................
Up to 102 .........
$9,691,530 to
$9,891,042.
Up to $24,480.
73 to 79 ............
$0 .....................
74 .....................
$432,160 to $467,680.
44 .....................
$4,112 ..............
$5,840 to
$6,320.
$7,632 ..............
74 .....................
$564,768.
1 .......................
$0 .....................
$80 ...................
102 ...................
$8,160.
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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 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 this 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.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
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.
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Boeing: Docket No. FAA–2009–0454;
Directorate Identifier 2008–NM–156–AD.
Comments Due Date
(a) We must receive comments by July 17,
2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747–
400, 747–400D, and 747–400F series
airplanes, certificated in any category; as
identified in Boeing Alert Service Bulletins
747–28A2280, dated August 7, 2008, and
747–28A2281, dated December 13, 2007.
Note 1: This AD requires revisions to
certain operator maintenance documents to
include a new inspection. Compliance with
this inspection is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by this inspection, the
operator may not be able to accomplish the
inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c),
the operator must request approval for an
alternative method of compliance (AMOC)
according to paragraph (m) of this AD. The
request should include a description of
changes to the required inspection that will
ensure the continued operational safety of
the airplane.
Subject
(d) Air Transport Association (ATA) of
America Code 28: Fuel.
Unsafe Condition
(e) This AD results from fuel system
reviews conducted by the manufacturer. We
are issuing this AD to prevent uncommanded
operation of certain override/jettison pumps
which could cause overheat, electrical arcs,
or frictional sparks, and could lead to an
ignition source inside a fuel tank. This
condition, in combination with flammable
fuel vapors, could result in a fuel tank
explosion and consequent loss of the
airplane.
Compliance
(f) Comply with this AD within the
compliance times specified, unless already
done.
Installations and Wiring Changes
(g) Within 60 months after the effective
date of this AD, do the actions in paragraphs
(g)(1) and (g)(2) of this AD, as applicable.
(1) For Model 747–400, –400D, and –400F
series airplanes: Install new pump control
and time delay relays and do related
investigative and all applicable corrective
actions, and change the wiring for the center
and main fuel tanks override/jettison fuel
pumps, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–28A2280, dated August
7, 2008. Do all related investigative and
applicable corrective actions before further
flight.
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(2) For Model 747–400 series airplanes:
Install new relays and wiring for the
horizontal stabilizer override/jettison fuel
pumps in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–28A2281, dated
December 13, 2007.
Prior/Concurrent Requirements
(h) Prior to or concurrently with the
actions required by paragraph (g) of this AD,
do the applicable actions in paragraphs (h)(1)
and (h)(2) of this AD.
(1) For Model 747–400, –400D, and –400F
series airplanes identified in paragraphs
(h)(1)(i), (h)(1)(ii), and (h)(1)(iii) of this AD:
Install a new integrated display system (IDS)
in accordance with the Accomplishment
Instructions of the applicable service bulletin
listed in paragraph (h)(1)(i), (h)(1)(ii), or
(h)(1)(iii) of this AD.
(i) For Model 747–400, –400D, and –400F
series airplanes that have General Electric
engines except airplanes having variable
numbers (V/Ns) RL429, RL430, RL473,
RL511, and RL521: Boeing Service Bulletin
747–31–2376, dated September 5, 2006.
(ii) For Model 747–400 and –400F series
airplanes that have Pratt & Whitney engines
except airplanes having V/Ns RL456, RL492,
and RL502: Boeing Service Bulletin 747–31–
2377, dated September 5, 2006.
(iii) For Model 747–400 and –400F series
airplanes that have Rolls Royce engines:
Boeing Service Bulletin 747–31–2378, dated
September 5, 2006.
(2) For Model 747–400 series airplanes
except V/Ns RM403, RM441 through RM443
inclusive, and RM445: Install a new
automatic shutoff system for the horizontal
stabilizer tank (HST) fuel pumps in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747–
28A2262, Revision 1, dated May 8, 2008.
Installations accomplished before the
effective date of this AD in accordance with
Boeing Service Bulletin 747–28A2262, dated
March 15, 2007, are acceptable for
compliance with the installation required by
this paragraph.
Maintenance Program Revision
(i) Concurrently with accomplishing the
actions required by paragraph (g) of this AD,
revise the maintenance program by
incorporating Airworthiness Limitation
(AWL) No. 28–AWL–24 and No. 28–AWL–26
of Section 9, ‘‘Airworthiness Limitations
(AWLs) and Certification Maintenance
Requirements (CMRs),’’ Boeing 747–400
Maintenance Planning (MPD) Data Document
D621U400–9, Revision April 2008. The
inspection interval for AWL No. 28–AWL–24
and AWL No. 28–AWL–26 starts on the date
the modification is incorporated.
No Alternative Inspections or Inspection
Intervals
(j) After accomplishing the action specified
in paragraph (i) of this AD, no alternative
actions or intervals may be used unless the
inspections or inspection intervals are
approved as an AMOC in accordance with
the procedures specified in paragraph (m) of
this AD.
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Acceptable Action for Certain ADs
(k) For Model 747–400, –400D, and –400F
series airplanes: Installing a new IDS in
accordance with paragraph (h)(1) of this AD
is an acceptable method of compliance for
the action in the applicable AD paragraph
listed in Table 1 of this AD.
TABLE 1—ACTIONS FOR WHICH PARAGRAPH (H)(1) OF THIS AD IS AN ACCEPTABLE METHOD OF COMPLIANCE (NO
CERTIFICATE LIMITATIONS)
The action in—
Of—
(1)
(2)
(3)
(4)
(5)
(6)
(7)
AD
AD
AD
AD
AD
AD
AD
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
E ..........................................................................................................................
(b) ........................................................................................................................
(d)(1) ....................................................................................................................
(a)(3)(iii) ...............................................................................................................
(a)(2)(ii) ................................................................................................................
(d)(2)(iv) ...............................................................................................................
(d)(1) ....................................................................................................................
(l) For Model 747–400, –400D, and –400F
series airplanes with a horizontal stabilizer
fuel tank and with horizontal stabilizer tank
fuel pump auto-shutoff installed: Installing a
new IDS in accordance with paragraph (h)(1)
of this AD is an acceptable method of
compliance for the action in the applicable
AD paragraph listed in Table 2 of this AD,
provided the certificate limitations included
in the following statement are incorporated
into the Limitations Section of the applicable
airplane flight manual (AFM) in place of the
certificate limitation required by the AFM
revision specified in the applicable AD listed
in Table 2 of this AD. This may be done by
inserting a copy of this AD in the AFM.
‘‘Certificate Limitations
Center Wing Tank
The center wing tank (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
pump(s) 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
The following additional limitations must
be followed if the horizontal stabilizer tank
is fueled and used:
The horizontal stabilizer tank (HST) fuel
quantity indication system must be operative
to dispatch with HST mission fuel.
If either the FUEL PMP STB L or R message
is displayed while on the ground, both HST
pumps must be selected OFF.
If either the FUEL PRES STB L or R
message is displayed, both HST pumps must
be selected OFF.
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 center wing tank, 3,000
pounds (1,400 kilograms) for main tanks, and
2,100 pounds (1,000 kilograms) for the
horizontal stabilizer tank. (These
requirements apply for defueling or
transferring between tanks.)
Warnings and Notes Applicable to All Fuel
Operations
Warning
Do not reset a tripped fuel pump circuit
breaker.
Warning
Do not cycle CWT and HST pump switches
from ON to OFF to ON with any continuous
low pressure indication present.
90–09–06, amendment 39–6581.
91–13–10 R1, amendment 39–8158.
96–07–09, amendment 39–9558.
2000–02–22, amendment 39–11540.
2000–12–21, amendment 39–11799.
2003–16–16, amendment 39–13269.
2004–10–05, amendment 39–13635.
Note
There is no change to the maximum zero
fuel gross weight found in the airplane flight
manual.
Note
In a low fuel situation, both CWT override/
jettison pumps may be selected ON and all
CWT fuel may be used.
Note
In a low fuel situation, both HST transfer
pumps may be selected ON and all HST fuel
may be used.
Note
The CWT and the HST may be emptied
normally during an emergency.
Note
The limitations contained in these
certificate limitations supersede any
conflicting basic airplane flight manual
limitations.’’
Note 2: When a statement identical to that
in paragraph (l) of this AD has been included
in the general revisions of the AFM, the
general revisions may be inserted into the
AFM, and the copy of this AD may be
removed from the AFM.
Note 3: The certificate limitations in
paragraph (l) of this AD are also included as
an enclosure to FAA Letter 140S–06–343,
dated November 17, 2006.
TABLE 2—ACTIONS FOR WHICH PARAGRAPH (H)(1) OF THIS AD IS AN ACCEPTABLE METHOD OF COMPLIANCE (WITH
CERTIFICATE LIMITATIONS)
The action in—
Of—
(1)
(2)
(3)
(4)
AD
AD
AD
AD
Paragraph
Paragraph
Paragraph
Paragraph
(a) ........................................................................................................................
(a) ........................................................................................................................
(c)(2) ....................................................................................................................
(a) ........................................................................................................................
Alternative Methods of Compliance
(AMOCs)
(m)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this
AD, if requested using the procedures
VerDate Nov<24>2008
16:00 Jun 01, 2009
Jkt 217001
found in 14 CFR 39.19. Send
information to ATTN: Jon Regimbal,
Aerospace Engineer, Propulsion Branch,
ANM–140S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue,
SW., Renton, Washington 98057–3356;
PO 00000
Frm 00020
Fmt 4702
Sfmt 4702
2001–12–21,
2001–21–07,
2002–19–52,
2002–24–52,
amendment
amendment
amendment
amendment
39–12277.
39–12478.
39–12900.
39–12993.
telephone (425) 917–6506; fax (425)
917–6590. Or, e-mail information to 9ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) To request a different method of
compliance or a different compliance
E:\FR\FM\02JNP1.SGM
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Federal Register / Vol. 74, No. 104 / Tuesday, June 2, 2009 / Proposed Rules
time for this AD, follow the procedures
in 14 CFR 39.19. Before using any
approved AMOC on any airplane to
which the AMOC applies, notify your
principal maintenance inspector (PMI)
or principal avionics inspector (PAI), as
appropriate, or lacking a principal
inspector, your local Flight Standards
District Office. The AMOC approval
letter must specifically reference this
AD.
Issued in Renton, Washington, on May 11,
2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–12742 Filed 6–1–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0496; Directorate
Identifier 2008–NM–139–AD]
RIN 2120–AA64
Airworthiness Directives; Fokker
Model F.27 Mark 050 and F.28 Mark
0100 Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
Several incidents have been reported
where an electrical burning smell was noted
in the cockpit, originating from the Electrical
Power Centre. Troubleshooting revealed a
partly molten terminal, which normally
attaches a wire or bus bar to a stud of an
Electrical Power Contactor, Part Number
(P/N) SG02206. Furthermore, heat damage to
the contactor stud itself was found. * * *
*
*
*
*
*
This condition, if not corrected, could lead
to further cases of overheating of terminals
and studs of Electrical Power Contactors
P/N SG02206, possibly resulting in the loss
of electrical power systems, electrical arcing
and fire/smoke in the cockpit.
The proposed AD would require
actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by July 2, 2009.
VerDate Nov<24>2008
16:00 Jun 01, 2009
Jkt 217001
You may send comments 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
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For Fokker service information
identified in this proposed AD, contact
Fokker Services B.V., Technical
Services Dept., P.O. Box 231, 2150 AE
Nieuw-Vennep, the Netherlands;
telephone +31 (0) 252–627–350; fax +31
(0) 252–627–211; e-mail
technicalservices.
fokkerservices@stork.com; Internet
https://www.myfokkerfleet.com.
For Goodrich service information
identified in this proposed AD, contact
Goodrich Corporation, Power Systems,
1555 Corporate Woods Parkway,
Uniontown, Ohio 44685–8799;
telephone 330–487–2007; fax 330–487–
1902; e-mail twinsburg.
techpubs@goodrich.com; Internet https://
www.goodrich.com/TechPubs.
You may review copies of the
referenced service information at the
FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA,
call 425–227–1221 or 425–227–1152.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1137; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
PO 00000
Frm 00021
Fmt 4702
Sfmt 4702
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2009–0496; Directorate Identifier
2008–NM–139–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on 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 proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2008–0091,
dated May 13, 2008 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
Several incidents have been reported
where an electrical burning smell was noted
in the cockpit, originating from the Electrical
Power Centre. Troubleshooting revealed a
partly molten terminal, which normally
attaches a wire or bus bar to a stud of an
Electrical Power Contactor, Part Number
(P/N) SG02206. Furthermore, heat damage to
the contactor stud itself was found. Material
investigation revealed that the terminal,
which was attached to the stud, was not
properly torque tightened when the incident
occurred. Loss of torque is considered to
have occurred during operation, for reasons
not fully understood. Further loosening may
have taken place in-service under influence
of vibration. As a result, poor contact caused
electrical arcing during which extremely high
temperatures were developed, leading to
partial melting of the terminal.
Investigation of some other burned
contactors revealed evidence (flat spring lock
washer) of a fully torqued terminal/stud
connection when the overheating occurred.
The exact cause for the increase in
temperature in the contactor and the
terminal/stud could not be determined.
However, it could not be excluded that an
increase of the temperature inside the
contactor could lead to reduction of the
reliability of the contactor stud/terminal
connection due to loss of lock washer
tension. The affected Electrical Power
Contactor is used on several locations in the
electrical power system, i.e. Generator Line
Contactor (GLC), Bus Tie Contactor (BTC),
Auxiliary Power Contactor (APC) and
External Power Contactor (EPC).
E:\FR\FM\02JNP1.SGM
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]]>Agencies
[Federal Register Volume 74, Number 104 (Tuesday, June 2, 2009)]
[Proposed Rules]
[Pages 26317-26322]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-12742]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0454; Directorate Identifier 2008-NM-156-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-400, 747-400D, and
747-400F Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Boeing Model 747-400, 747-400D, and 747-400F series airplanes.
For all airplanes, this proposed AD would require installing new pump
control and time delay relays, doing related investigative and
corrective actions if necessary, and changing the wiring for the center
and main fuel tanks override/jettison fuel pumps; and, for certain
airplanes, installing new relays and wiring for the horizontal
stabilizer override/jettison fuel pumps. This proposed AD would also
require a revision to the maintenance program to incorporate
Airworthiness Limitation No. 28-AWL-24 and No. 28-AWL-26. For certain
airplanes, this proposed AD would also require installing an automatic
shutoff system for the horizontal stabilizer tank fuel pumps and
installing a new integrated display system. This proposed AD results
from fuel system reviews conducted by the manufacturer. We are
proposing this AD to prevent uncommanded operation of certain override/
jettison pumps which could cause overheat, electrical arcs, or
frictional sparks, and could lead to an ignition source inside a fuel
tank. This condition, in combination with flammable fuel vapors, could
result in a fuel tank explosion and consequent loss of the airplane.
DATES: We must receive comments on this proposed AD by July 17, 2009.
ADDRESSES: You may send comments 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.
For service information identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data & Services Management, P.O. Box
3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000,
extension 1, fax 206-766-5680; e-mail me.boecom@boeing.com; Internet
https://www.myboeingfleet.com.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; 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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Jon Regimbal, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 917-6506; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0454;
Directorate Identifier 2008-NM-156-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed 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 proposed AD.
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
[[Page 26318]]
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'' (66 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 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 a 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.
Safety assessments conducted by Boeing indicate that there is a
risk of an ignition source in the main and center fuel tanks for Model
747-400, 747-400D, and 747-400F series airplanes, and in the horizontal
stabilizer fuel tanks of Model 747-400 series airplanes, if the
override/jettison pump continues to run for an extended time after the
fuel level goes below the pump inlet. The pump is normally commanded
off if the fuel level goes below the pump inlet, but if a single
failure in the pump control circuitry occurs, a pump can continue to
run after it is commanded off. Uncommanded operation of certain
override/jettison pumps could cause overheat, electrical arcs, or
frictional sparks, and could lead to an ignition source inside a fuel
tank. This condition, in combination with flammable fuel vapors, could
result in a fuel tank explosion and consequent loss of the airplane.
Other Related Rulemaking
Installing a new integrated display system (IDS) in accordance with
Boeing Service Bulletin 747-31-2376, 747-31-2377, or 747-31-2378, all
dated September 5, 2006, as applicable, would provide an acceptable
substitute for complying with certain paragraphs of the ADs listed
below.
Paragraph E. of AD 90-09-06, amendment 39-6581 (55 FR
15217, April 23, 1990). That AD applies to all Model 747 series
airplanes and requires, among other actions, installing a system to
provide visual warning signals to alert flightcrew members and ground
crew personnel of certain incorrect indications.
Paragraph (b) of AD 91-13-10 R1, amendment 39-8158 (57 FR
2446, January 22, 1992). That AD applies to certain Boeing Model 747
and 767 series airplanes and requires, among other actions, replacing
the engine indicating and crew alerting system (EICAS) computers.
Paragraph (d)(1) of AD 96-07-09, amendment 39-9558 (61 FR
14608, April 3, 1996). That AD applies to all Boeing Model 747-400,
757, and 767 series airplanes and requires, among other actions,
installing an upgraded EICAS computer that provides ``advisory''
messages to the flightcrew to indicate an impending engine fuel filter
bypass condition for each engine.
Paragraph (a)(3)(iii) of AD 2000-02-22, amendment 39-11540
(65 FR 5222, February 3, 2000). That AD applies to certain Boeing Model
747-400 series airplanes and requires, among other actions, modifying
the IDS software.
Paragraph (a)(2)(ii) of AD 2000-12-21, amendment 39-11799
(65 FR 39079, June 23, 2000). [A correction of that AD was published in
the Federal Register on July 18, 2000 (65 FR 44432).] That AD requires,
among other actions, modifying the IDS software.
Paragraph (d)(2)(iv) of AD 2003-16-16, amendment 39-13269
(68 FR 51439, August 27, 2003). That AD applies to certain Boeing Model
747-400 series airplanes and requires, among other actions, installing
new IDS software in six integrated display units and three electronic
flight information (EFI)/EICAS interface units.
Paragraph (d)(1) of AD 2004-10-05, amendment 39-13635 (69
FR 28052, May 18, 2004). That AD applies to certain Boeing Model 747-
400, 747-400D, 747-400F, 757-200, 757-200PF, 757-200CB, 767-200, 767-
300, and 767-300F series airplanes. That AD requires, among other
actions for Model 747-400, -400D, and -400F series airplanes, replacing
the three EFIS/EICAS interface units (EIU), installing new software in
the integrated display units (IDUs) and EIUs, replacing certain central
maintenance computers (CMCs), and installing new software in the CMCs.
For airplanes with a horizontal stabilizer fuel tank and with
horizontal stabilizer tank fuel pump auto-shutoff installed, installing
a new IDS in accordance with Boeing Service Bulletin 747-31-2376, 747-
31-2377, or 747-31-2378, all dated September 5, 2006, as applicable,
would provide an acceptable method for complying with certain
paragraphs of the ADs listed below, provided the certificate
limitations enclosed with FAA Letter 140S-06-343, dated November 17,
2006, are incorporated into the limitations section of the applicable
airplane flight manual (AFM) revision specified in the applicable AD.
Paragraph (a) of AD 2001-12-21, amendment 12777 (66 FR
33170, June 21, 2001). That AD applies to all Boeing Model 747 series
airplanes and requires, among other actions, revising the Limitations
Section of the AFM to include procedures to prevent dry operation of
the center wing fuel tank override/jettison pumps and, for certain
airplanes, to prohibit operation of the horizontal stabilizer tank
transfer pumps in-flight.
Paragraph (a) of AD 2001-21-07, amendment 39-12478 (66 FR
54652, October 30, 2001). That AD applies to certain Boeing Model 747
series airplanes and requires, among other actions, revising the AFM to
specify the amount of fuel necessary for operating the override/
jettison fuel pumps, and to specify not resetting the circuit breakers
for the override/jettison fuel pumps if they are tripped.
Paragraph (c)(2) of AD 2002-19-52, amendment 39-12900 (67
FR 61253, September 30, 2002). That AD applies to all Boeing Model 737-
600, -700, -700C, -800, and -900 series airplanes; Model 747 series
airplanes; and Model 757 series airplanes. That AD requires, among
other actions, revising the AFM
[[Page 26319]]
to advise the flightcrew of certain operating restrictions for
maintaining minimum fuel levels.
Paragraph (a) of AD 2002-24-52, amendment 39-12993 (68 FR
14, January 2, 2003). That AD applies to all Boeing Model 747-400, -
400D, and -400 F series airplanes and requires, among other actions,
revising the AFM to require the flightcrew to maintain certain minimum
fuel levels in the center wing fuel tank, and to prohibit the use of
the horizontal stabilizer fuel tank.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-28A2280, dated
August 7, 2008. This service bulletin describes procedures for
installing new pump control and time delay relays, doing related
investigative and corrective actions if necessary, and changing the
wiring for the center and main fuel tanks override/jettison fuel pumps.
The related investigative and corrective actions include doing a
general visual inspection for corrosion of the ground stud assembly
during the installation of the P914 relay panel and cleaning or
replacing the ground stud assembly if necessary. Boeing Alert Service
Bulletin 747-28A2280 specifies that the installation of a new
integrated display system (IDS), as described in the following service
bulletins, must be done before or at the same time as the actions in
the alert service bulletin:
Boeing Service Bulletin 747-31-2376, dated September 5,
2006, for Model 747-400, and -400F series airplanes that have General
Electric engines, except for airplanes having variable numbers (V/Ns)
RL429, RL430, RL473, RL511, and RL521, which received new software in
production.
Boeing Service Bulletin 747-31-2377, dated September 5,
2006, for Model 747-400, and -400F series airplanes that have Pratt &
Whitney engines, except for airplanes having V/Ns RL456, RL492, and
RL502, which received new software in production.
Boeing Service Bulletin 747-31-2378, dated September 5,
2006, for Model 747-400, -400D, and -400F series airplanes that have
Rolls Royce engines.
We have also reviewed Boeing Alert Service Bulletin 747-28A2281,
dated December 13, 2007, for Model 747-400 series airplanes. This
service bulletin describes procedures for installing new relays and
wiring in the horizontal stabilizer override/jettison fuel pumps.
Boeing Alert Service Bulletin 747-28A2281 specifies that the
installation of a new automatic shutoff system for the horizontal
stabilizer tank (HST) fuel pumps, as described in the following service
bulletin, must be done before or at the same time as the actions in the
alert service bulletin: Boeing Service Bulletin 747-28A2262, Revision
1, dated May 8, 2008, for Model 747-400 series airplanes, except for
airplanes having V/Ns RM403, RM441, RM442, RM443, and RM445.
We have also reviewed Section 9, ``Airworthiness Limitations (AWLs)
and Certification Maintenance Requirements (CMRs),'' Boeing 747-400
Maintenance Planning (MPD) Data Document D621U400-9, Revision April
2008 (hereafter referred to as ``Document D621U400-9''). Sub-section D
of Document D621U400-9 describes AWLs for fuel tank systems. Sub-
section D of Document D621U400-9 includes the following fuel system
AWLs:
AWL No. 28-AWL-24, which is a repetitive functional test
to verify continued functionality of the automatic shutoff system for
the fuel boost pump of the HST. This AWL applies to Model 747-400
airplanes, line numbers (L/Ns) 1343 and subsequent, and those that have
been modified in accordance with Boeing Service Bulletin 747-28A2262.
AWL No. 28-AWL-26, which is a repetitive operational test
to verify the continued functionality of the uncommanded on system for
the override/jettison pump of the main 2 and main 3 fuel tanks. This
AWL applies to Model 747-400, -400D, and -400F airplanes, L/Ns 1380 and
subsequent, and those that have been modified in accordance with Boeing
Alert Service Bulletin 747-28A2280.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
This proposed AD would require, for all airplanes installing new pump
control and time delay relays, doing related investigative and
corrective actions if necessary, and changing the wiring for the center
and main fuel tanks override/jettison fuel pumps; and, for certain
airplanes, installing new relays and wiring for the horizontal
stabilizer override/jettison fuel pumps. This proposed AD would also
require a revision to the maintenance program to incorporate
Airworthiness Limitation No. 28-AWL-24 and No. 28-AWL-26. For certain
airplanes, this proposed AD would also require installing an automatic
shutoff system for the horizontal stabilizer tank fuel pumps and
installing a new integrated display system.
Costs of Compliance
We estimate that this proposed AD would affect 102 airplanes of
U.S. registry. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD. The average labor rate
is $80 per work hour.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Parts Cost per product registered airplanes Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
Installing relays/changing wiring 375 to 394............ $65,015 to $65,451.... $95,015 to $96,971... 102.................. $9,691,530 to
for center and main fuel tanks. $9,891,042.
Installing a new IDS and revising 2 to 3................ $0.................... Up to $240........... Up to 102............ Up to $24,480.
the AFM when done (prior/
concurrent action).
Installing relays and wiring for 73 to 79.............. $0.................... $5,840 to $6,320..... 74................... $432,160 to $467,680.
horizontal stabilizer tank (HST).
Installing a new automatic shutoff 44.................... $4,112................ $7,632............... 74................... $564,768.
for the HST.
Revising the maintenance program... 1..................... $0.................... $80.................. 102.................. $8,160.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 26320]]
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 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 this 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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, 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 FAA amends Sec. 39.13 by adding the following new AD:
Boeing: Docket No. FAA-2009-0454; Directorate Identifier 2008-NM-
156-AD.
Comments Due Date
(a) We must receive comments by July 17, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747-400, 747-400D, and 747-
400F series airplanes, certificated in any category; as identified
in Boeing Alert Service Bulletins 747-28A2280, dated August 7, 2008,
and 747-28A2281, dated December 13, 2007.
Note 1: This AD requires revisions to certain operator
maintenance documents to include a new inspection. Compliance with
this inspection is required by 14 CFR 91.403(c). For airplanes that
have been previously modified, altered, or repaired in the areas
addressed by this inspection, the operator may not be able to
accomplish the inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance (AMOC)
according to paragraph (m) of this AD. The request should include a
description of changes to the required inspection that will ensure
the continued operational safety of the airplane.
Subject
(d) Air Transport Association (ATA) of America Code 28: Fuel.
Unsafe Condition
(e) This AD results from fuel system reviews conducted by the
manufacturer. We are issuing this AD to prevent uncommanded
operation of certain override/jettison pumps which could cause
overheat, electrical arcs, or frictional sparks, and could lead to
an ignition source inside a fuel tank. This condition, in
combination with flammable fuel vapors, could result in a fuel tank
explosion and consequent loss of the airplane.
Compliance
(f) Comply with this AD within the compliance times specified,
unless already done.
Installations and Wiring Changes
(g) Within 60 months after the effective date of this AD, do the
actions in paragraphs (g)(1) and (g)(2) of this AD, as applicable.
(1) For Model 747-400, -400D, and -400F series airplanes:
Install new pump control and time delay relays and do related
investigative and all applicable corrective actions, and change the
wiring for the center and main fuel tanks override/jettison fuel
pumps, in accordance with the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-28A2280, dated August 7, 2008. Do all
related investigative and applicable corrective actions before
further flight.
(2) For Model 747-400 series airplanes: Install new relays and
wiring for the horizontal stabilizer override/jettison fuel pumps in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-28A2281, dated December 13, 2007.
Prior/Concurrent Requirements
(h) Prior to or concurrently with the actions required by
paragraph (g) of this AD, do the applicable actions in paragraphs
(h)(1) and (h)(2) of this AD.
(1) For Model 747-400, -400D, and -400F series airplanes
identified in paragraphs (h)(1)(i), (h)(1)(ii), and (h)(1)(iii) of
this AD: Install a new integrated display system (IDS) in accordance
with the Accomplishment Instructions of the applicable service
bulletin listed in paragraph (h)(1)(i), (h)(1)(ii), or (h)(1)(iii)
of this AD.
(i) For Model 747-400, -400D, and -400F series airplanes that
have General Electric engines except airplanes having variable
numbers (V/Ns) RL429, RL430, RL473, RL511, and RL521: Boeing Service
Bulletin 747-31-2376, dated September 5, 2006.
(ii) For Model 747-400 and -400F series airplanes that have
Pratt & Whitney engines except airplanes having V/Ns RL456, RL492,
and RL502: Boeing Service Bulletin 747-31-2377, dated September 5,
2006.
(iii) For Model 747-400 and -400F series airplanes that have
Rolls Royce engines: Boeing Service Bulletin 747-31-2378, dated
September 5, 2006.
(2) For Model 747-400 series airplanes except V/Ns RM403, RM441
through RM443 inclusive, and RM445: Install a new automatic shutoff
system for the horizontal stabilizer tank (HST) fuel pumps in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 747-28A2262, Revision 1, dated May 8, 2008. Installations
accomplished before the effective date of this AD in accordance with
Boeing Service Bulletin 747-28A2262, dated March 15, 2007, are
acceptable for compliance with the installation required by this
paragraph.
Maintenance Program Revision
(i) Concurrently with accomplishing the actions required by
paragraph (g) of this AD, revise the maintenance program by
incorporating Airworthiness Limitation (AWL) No. 28-AWL-24 and No.
28-AWL-26 of Section 9, ``Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements (CMRs),'' Boeing 747-400
Maintenance Planning (MPD) Data Document D621U400-9, Revision April
2008. The inspection interval for AWL No. 28-AWL-24 and AWL No. 28-
AWL-26 starts on the date the modification is incorporated.
No Alternative Inspections or Inspection Intervals
(j) After accomplishing the action specified in paragraph (i) of
this AD, no alternative actions or intervals may be used unless the
inspections or inspection intervals are approved as an AMOC in
accordance with the procedures specified in paragraph (m) of this
AD.
[[Page 26321]]
Acceptable Action for Certain ADs
(k) For Model 747-400, -400D, and -400F series airplanes:
Installing a new IDS in accordance with paragraph (h)(1) of this AD
is an acceptable method of compliance for the action in the
applicable AD paragraph listed in Table 1 of this AD.
Table 1--Actions for Which Paragraph (h)(1) of This AD Is an Acceptable Method of Compliance (No Certificate
limitations)
----------------------------------------------------------------------------------------------------------------
The action in-- Of--
----------------------------------------------------------------------------------------------------------------
(1) Paragraph E........................ AD 90-09-06, amendment 39-6581.
(2) Paragraph (b)...................... AD 91-13-10 R1, amendment 39-8158.
(3) Paragraph (d)(1)................... AD 96-07-09, amendment 39-9558.
(4) Paragraph (a)(3)(iii).............. AD 2000-02-22, amendment 39-11540.
(5) Paragraph (a)(2)(ii)............... AD 2000-12-21, amendment 39-11799.
(6) Paragraph (d)(2)(iv)............... AD 2003-16-16, amendment 39-13269.
(7) Paragraph (d)(1)................... AD 2004-10-05, amendment 39-13635.
----------------------------------------------------------------------------------------------------------------
(l) For Model 747-400, -400D, and -400F series airplanes with a
horizontal stabilizer fuel tank and with horizontal stabilizer tank
fuel pump auto-shutoff installed: Installing a new IDS in accordance
with paragraph (h)(1) of this AD is an acceptable method of
compliance for the action in the applicable AD paragraph listed in
Table 2 of this AD, provided the certificate limitations included in
the following statement are incorporated into the Limitations
Section of the applicable airplane flight manual (AFM) in place of
the certificate limitation required by the AFM revision specified in
the applicable AD listed in Table 2 of this AD. This may be done by
inserting a copy of this AD in the AFM.
``Certificate Limitations
Center Wing Tank
The center wing tank (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 pump(s) 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
The following additional limitations must be followed if the
horizontal stabilizer tank is fueled and used:
The horizontal stabilizer tank (HST) fuel quantity indication
system must be operative to dispatch with HST mission fuel.
If either the FUEL PMP STB L or R message is displayed while on
the ground, both HST pumps must be selected OFF.
If either the FUEL PRES STB L or R message is displayed, both
HST pumps must be selected OFF.
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 center wing tank, 3,000 pounds
(1,400 kilograms) for main tanks, and 2,100 pounds (1,000 kilograms)
for the horizontal stabilizer tank. (These requirements apply for
defueling or transferring between tanks.)
Warnings and Notes Applicable to All Fuel Operations
Warning
Do not reset a tripped fuel pump circuit breaker.
Warning
Do not cycle CWT and HST pump switches from ON to OFF to ON with
any continuous low pressure indication present.
Note
There is no change to the maximum zero fuel gross weight found
in the airplane flight manual.
Note
In a low fuel situation, both CWT override/jettison pumps may be
selected ON and all CWT fuel may be used.
Note
In a low fuel situation, both HST transfer pumps may be selected
ON and all HST fuel may be used.
Note
The CWT and the HST may be emptied normally during an emergency.
Note
The limitations contained in these certificate limitations
supersede any conflicting basic airplane flight manual
limitations.''
Note 2: When a statement identical to that in paragraph (l) of
this AD has been included in the general revisions of the AFM, the
general revisions may be inserted into the AFM, and the copy of this
AD may be removed from the AFM.
Note 3: The certificate limitations in paragraph (l) of this AD
are also included as an enclosure to FAA Letter 140S-06-343, dated
November 17, 2006.
Table 2--Actions for Which Paragraph (h)(1) of This AD Is an Acceptable Method of Compliance (With Certificate
Limitations)
----------------------------------------------------------------------------------------------------------------
The action in-- Of--
----------------------------------------------------------------------------------------------------------------
(1) Paragraph (a)...................... AD 2001-12-21, amendment 39-12277.
(2) Paragraph (a)...................... AD 2001-21-07, amendment 39-12478.
(3) Paragraph (c)(2)................... AD 2002-19-52, amendment 39-12900.
(4) Paragraph (a)...................... AD 2002-24-52, amendment 39-12993.
----------------------------------------------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(m)(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. Send information to ATTN: Jon
Regimbal, Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 917-6506; fax (425) 917-6590.
Or, e-mail information to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) To request a different method of compliance or a different
compliance
[[Page 26322]]
time for this AD, follow the procedures in 14 CFR 39.19. Before using
any approved AMOC on any airplane to which the AMOC applies, notify
your principal maintenance inspector (PMI) or principal avionics
inspector (PAI), as appropriate, or lacking a principal inspector, your
local Flight Standards District Office. The AMOC approval letter must
specifically reference this AD.
Issued in Renton, Washington, on May 11, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-12742 Filed 6-1-09; 8:45 am]
BILLING CODE 4910-13-P
