Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Airplanes, 46319-46322 [E9-20840]
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Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations
Related Information
(h) Refer to MCAI Canadian Airworthiness
Directive CF–2009–01, dated January 19,
2009; Bombardier Dash 8 Q400 TA 14, Issue
1, dated May 10, 2006; and Bombardier
Service Bulletin 84–61–03, Revision ‘A,’
dated September 18, 2008; for related
information.
Material Incorporated by Reference
(i) You must use Bombardier Dash 8 Q400
Temporary Amendment 14, Issue 1, dated
May 10, 2006; and Bombardier Service
Bulletin 84–61–03, Revision ‘A,’ dated
September 18, 2008; as applicable; to do the
actions required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; e-mail
thd.qseries@aero.bombardier.com; Internet
https://www.bombardier.com.
(3) You may review copies of the 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.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on August
18, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–20836 Filed 9–8–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0563; Directorate
Identifier 2008–NM–180–AD; Amendment
39–16005; AD 2009–18–09]
jlentini on DSKJ8SOYB1PROD with RULES
Airworthiness Directives; Fokker
Model F.28 Mark 0070 and 0100
Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are superseding an
existing airworthiness directive (AD) for
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Jkt 217001
A recent design review has been carried
out on the F28 Mark 0070/0100 fuel system
in accordance with the guidelines related to
FAA SFAR 88 [Special Federal Aviation
Regulation No. 88] (Fuel Tank Safety
Program) and JAA [Joint Aviation
Authorities] INT/POL/25/12. The review
revealed that under certain failure
conditions, prolonged dry running of the fuel
transfer pumps may result in an ignition
source in the centre wing fuel tank. This
condition, if not corrected, could lead to
ignition of flammable fuel vapors, resulting
in fuel tank explosion and consequent loss of
the aircraft.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
October 14, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 14, 2009.
On October 27, 1999 (64 FR 51202,
September 22, 1999), the Director of the
Federal Register approved the
incorporation by reference of certain
other publications listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
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:
Discussion
RIN 2120–AA64
VerDate Nov<24>2008
the products listed above. This 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:
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on June 19, 2009 (74 FR 29144),
and proposed to supersede AD 99–20–
01, Amendment 39–11329 (64 FR
51202, September 22, 1999). That NPRM
proposed to correct an unsafe condition
for the specified products. The MCAI
states:
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46319
A recent design review has been carried
out on the F28 Mark 0070/0100 fuel system
in accordance with the guidelines related to
FAA SFAR 88 [Special Federal Aviation
Regulation No. 88] (Fuel Tank Safety
Program) and JAA [Joint Aviation
Authorities] INT/POL/25/12. The review
revealed that under certain failure
conditions, prolonged dry running of the fuel
transfer pumps may result in an ignition
source in the centre wing fuel tank. This
condition, if not corrected, could lead to
ignition of flammable fuel vapors, resulting
in fuel tank explosion and consequent loss of
the aircraft.
To address and correct this unsafe
condition, new software (version V13.55) has
been developed for the Flight Warning
Computer (FWC). This software update
introduces a decreased time delay of the
centre wing fuel tank low pressure alert from
15 minutes to 60 seconds, to stop prolonged
dry running of the fuel transfer pumps.
For the reasons described above, this EASA
Airworthiness Directive (AD) requires the
replacement of the FWC with a modified
unit, incorporating software version V13.55.
The corrective actions include
revising the airplane flight manual
(AFM) to change certain indications and
warnings; installing new software for
the multifunction display unit (MFDU);
and installing a new resistor in the
thrust reverser indicator and control
system, or an improved thrust reverser
unlock indication relay. You may obtain
further information by examining the
MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a note within the AD.
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Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations
Costs of Compliance
We estimate that this AD affects about
4 products of U.S. registry.
The actions that are required by AD
99–20–01 and retained in this AD take
about 7 work-hours per product, at an
average labor rate of $80 per work hour.
Required parts cost about $1,593 per
product. Based on these figures, the
estimated cost of the currently required
actions is $2,153 per product.
We estimate that it takes about 7
work-hours per product to comply with
the new basic requirements of this AD.
The average labor rate is $80 per workhour. Required parts cost about $5,350
per product. Where the service
information lists required parts costs
that are covered under warranty, we
have assumed that there will be no
charge for these costs. As we do not
control warranty coverage for affected
parties, some parties may incur costs
higher than estimated here. Based on
these figures, we estimate the cost of
this AD to U.S. operators to be $23,640,
or $5,910 per product.
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.
jlentini on DSKJ8SOYB1PROD with RULES
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
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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 AD and placed it in the AD docket.
through 11537 inclusive, 11545, 11547,
11553, 11557, 11561, 11562, 11566, 11567,
11571, 11572, 11576 through 11579
inclusive, and 11581 through 11583
inclusive. All airplanes with these serial
numbers are fitted with center wing fuel
tanks.
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 the NPRM, 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.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
A recent design review has been carried
out on the F28 Mark 0070/0100 fuel system
in accordance with the guidelines related to
FAA SFAR 88 [Special Federal Aviation
Regulation No. 88] (Fuel Tank Safety
Program) and JAA [Joint Aviation
Authorities] INT/POL/25/12. The review
revealed that under certain failure
conditions, prolonged dry running of the fuel
transfer pumps may result in an ignition
source in the centre wing fuel tank. This
condition, if not corrected, could lead to
ignition of flammable fuel vapors, resulting
in fuel tank explosion and consequent loss of
the aircraft.
To address and correct this unsafe
condition, new software (version V13.55) has
been developed for the Flight Warning
Computer (FWC). This software update
introduces a decreased time delay of the
centre wing fuel tank low pressure alert from
15 minutes to 60 seconds, to stop prolonged
dry running of the fuel transfer pumps.
For the reasons described above, this EASA
Airworthiness Directive (AD) requires the
replacement of the FWC with a modified
unit, incorporating software version V13.55.
The corrective actions include revising the
airplane flight manual (AFM) to change
certain indications and warnings; installing
new software for the multifunction display
unit (MFDU); and installing a new resistor in
the thrust reverser indicator and control
system, or an improved thrust reverser
unlock indication relay.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–11329 (64 FR
51202, September 22, 1999) and adding
the following new AD:
■
2009–18–09 Fokker Services B.V.:
Amendment 39–16005. Docket No.
FAA–2009–0563; Directorate Identifier
2008–NM–180–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective October 14, 2009.
Affected ADs
(b) This AD supersedes AD 99–20–01,
Amendment 39–11329.
Applicability
(c) This AD applies to airplanes,
certificated in any category, as identified in
paragraphs (c)(1) and (c)(2) of this AD.
(1) Fokker Model F.28 Mark 0100
airplanes, all serial numbers.
(2) Fokker Model F.28 Mark 0070
airplanes, serial numbers 11521, 11528
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Subject
(d) Air Transport Association (ATA) of
America Codes 31 and 78: Instruments and
Engine Exhaust, respectively.
Restatement of Requirements of AD 99–20–
01 With No Changes to the Modifications
(f) Unless already done, within 18 months
after October 27, 1999 (the effective date of
AD 99–20–01), modify the electrical wiring
of the FWC in accordance with Part 1 or 2,
as applicable, of the Accomplishment
Instructions of Fokker Service Bulletin
SBF100–31–047, Revision 1, dated March 21,
1997.
Note 1: It is not necessary to install
computer software version V10.40 into the
FWC, since a later version is available and is
required to be installed by AD 99–20–01.
(g) Unless already done, concurrently with
the accomplishment of the requirements of
paragraph (f) of this AD, install upgraded
computer software version V11.45 into the
FWC in accordance with Fokker Service
Bulletin SBF100–31–051, dated August 15,
1998.
Note 2: AlliedSignal Grimes Aerospace has
issued Service Bulletin 80–0610–31–0031,
dated May 14, 1998, as an additional source
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of guidance for installation of the upgraded
computer software version into the FWC.
Note 3: Operators should note that Fokker
Service Bulletin SBF100–31–051, dated
August 15, 1998, specifies prior or
concurrent accomplishment of Fokker
Service Bulletin SBF100–78–014 (which
specifies concurrent accomplishment of
Fokker Component Service Bulletin (CSB)
P41440–78–04, and prior or concurrent
accomplishment of Fokker Service Bulletin
SBF100–78–012 and CSB P41440–78–05).
Related FAA AD 99–20–02, amendment 39–
11330, requires accomplishment of these four
other service bulletins.
New Requirements of This AD: Actions and
Compliance
(h) Unless already done, do the following
actions.
(1) Within 36 months after the effective
date of this AD, replace FWC units having
part number (P/N) 80–0610–3–45 and P/N
80–0610–3–50 with modified units having
P/N 80–0610–3–55, in accordance with the
Accomplishment Instructions of Fokker
Service Bulletin SBF100–31–067, Revision 1,
dated April 24, 2008.
(2) Within 36 months after the effective
date of this AD and concurrently with the
accomplishment of paragraph (h)(1) of this
AD, revise the Emergency and Abnormal
Procedures sections of the airplane flight
manual (AFM), as specified in Fokker
Manual Change Notification-Operational
Documentation MCNO–F100–050, dated
January 31, 2008, which is included in
Fokker Service Bulletin SBF100–31–067,
Revision 1, dated April 24, 2008. These AFM
sections provide alterations, which are
introduced in Fokker Service Bulletin
SBF100–31–067, Revision 1, dated April 24,
2008.
Note 4: Revisions to the Emergency
Procedures and Abnormal Procedures
sections of the AFM, as specified in Fokker
MCNO–F100–050, dated January 31, 2008,
may be done by inserting copies of Fokker
MCNO–F100–050, dated January 31, 2008,
into the AFM. When the information in
Fokker MCNO–F100–050, dated January 31,
2008, has been included in general revisions
of the AFM, the general revisions may be
inserted in the AFM, provided the relevant
information in the general revisions are
identical to that in Fokker MCNO–F100–050,
dated January 31, 2008.
(3) After accomplishing paragraph (h)(1) of
this AD, no person may install an FWC
having P/N 80–0610–3–45 or P/N 80–0610–
3–50, unless it has been modified to P/N 80–
0610–3–55 standard in accordance with
Honeywell Service Bulletin 80–0610–31–
0003, dated February 13, 2008.
(4) Within 36 months after the effective
date of this AD, install software version V12
for the MFDU in accordance with the
Accomplishment Instructions of Fokker
Service Bulletin SBF100–31–060, dated June
1, 2002.
(5) Within 36 months after the effective
date of this AD, modify the thrust reverser
indication and control system in accordance
with the Accomplishment Instructions of
Fokker Service Bulletin SBF100–78–016,
dated October 1, 1999; or modify the thrust
reverser unlock indication relay in
accordance with the Accomplishment
Instructions of Fokker Service Bulletin
SBF100–78–017, dated December 1, 1999.
FAA AD Differences
Note 5: This AD differs from the MCAI
and/or service information as follows:
(1) Replacing the MFDU in accordance
with Fokker Service Bulletin SBF100–31–
060, dated June 1, 2002, is not included in
the MCAI; however, this AD includes that
action. It is necessary to install a new version
of the MFDU software before installing the
new version of the FWC software.
(2) Modifying the thrust reverser indication
and control system in accordance with
Fokker Service Bulletin SBF100–78–016,
dated October 1, 1999; or modifying the
thrust reverser unlock indication relay in
accordance with Fokker Service Bulletin
SBF100–78–017, dated December 1, 1999, is
not included in the MCAI; however, this AD
46321
includes those actions. It is necessary to do
one of those actions before installing the
MFDU software.
Other FAA AD Provisions
(i) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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: 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. 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
(j) Refer to MCAI European Aviation Safety
Agency Airworthiness Directive 2008–0090,
dated May 13, 2008, and the service
information identified in Table 1 of this AD,
for related information.
TABLE 1—RELATED INFORMATION
Service information—
Revision level—
Dated—
Fokker Service Bulletin SBF100–31–047 ..........................
Fokker Service Bulletin SBF100–31–051 ..........................
Fokker Service Bulletin SBF100–31–060 ..........................
Fokker Service Bulletin SBF100–31–067, including
Fokker Manual Change Notification-Operational Documentation MCNO–F100–50, dated January 31, 2008.
Fokker Service Bulletin SBF100–78–016 ..........................
Fokker Service Bulletin SBF100–78–017 ..........................
1 .........................................................................................
Original ...............................................................................
Original ...............................................................................
1 .........................................................................................
March 21, 1997.
August 15, 1998.
June 1, 2002.
April 24, 2008.
Original ...............................................................................
Original ...............................................................................
October 1, 1999.
December 1, 1999.
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Material Incorporated by Reference
(k) You must use the service information
contained in Table 2 of this AD to do the
actions required by this AD, unless the AD
specifies otherwise.
TABLE 2—ALL MATERIAL INCORPORATED BY REFERENCE
Document
Revision
Fokker Service Bulletin SBF100–31–047 ..........................
Fokker Service Bulletin SBF100–31–051 ..........................
1 .........................................................................................
Original ...............................................................................
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Date
09SER1
March 21, 1997.
August 15, 1998.
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Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations
TABLE 2—ALL MATERIAL INCORPORATED BY REFERENCE—Continued
Document
Revision
Fokker Service Bulletin SBF100–31–060 ..........................
Fokker Service Bulletin SBF100–31–067, including
Fokker Manual Change Notification-Operational Documentation MCNO–F100–50, dated January 31, 2008.
Fokker Service Bulletin SBF100–78–016 ..........................
Fokker Service Bulletin SBF100–78–017 ..........................
Original ...............................................................................
1 .........................................................................................
June 1, 2002.
April 24, 2008.
Original ...............................................................................
Original ...............................................................................
October 1, 1999.
December 1, 1999.
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information contained in Table 3
Date
of this AD under 5 U.S.C. 552(a) and 1 CFR
part 51.
TABLE 3—NEW MATERIAL INCORPORATED BY REFERENCE
Document
Revision
Fokker Service Bulletin SBF100–31–060 ..........................
Fokker Service Bulletin SBF100–31–067, including
Fokker Manual Change Notification-Operational Documentation MCNO–F100–50, dated January 31, 2008.
Fokker Service Bulletin SBF100–78–016 ..........................
Fokker Service Bulletin SBF100–78–017 ..........................
Original ...............................................................................
1 .........................................................................................
June 1, 2002.
April 24, 2008.
Original ...............................................................................
Original ...............................................................................
October 1, 1999.
December 1, 1999.
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(2) The Director of the Federal Register
previously approved the incorporation by
reference of Fokker Service Bulletin SBF100–
31–047, Revision 1, dated March 21, 1997;
and Fokker Service Bulletin SBF100–31–051,
dated August 15, 1998; on October 27, 1999
(64 FR 51202, September 22, 1999).
(3) For Fokker service information
identified in this 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.
(4) For AlliedSignal Grimes Aerospace and
Honeywell service information identified in
this AD, contact Honeywell Aerospace,
Technical Publications and Distribution,
M/S 2101–201, P.O. Box 52170, Phoenix,
Arizona 85072–2170; telephone 602–365–
5535; fax 602–365–5577; Internet https://
www.honeywell.com.
(5) You may review copies of the 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.
(6) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on August
18, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–20840 Filed 9–8–09; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0381; Directorate
Identifier 2009–NM–008–AD; Amendment
39–16016; AD 2009–18–19]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–200 and –300 Series Airplanes
and Model A340–200 and –300 Series
Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This 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:
An A340 operator has reported an
uncommanded engine N°4 shut down during
taxi after landing.
The root cause of this event has been
identified as failure of the fuel pump Non
Return Valve (NRV) preventing the collector
cell jet pump from working. This led to
engine N°4 collector cell fuel level to drop
below the pump inlet and consequently
causing engine N°4 flame out.
*
*
*
*
*
Multiple NRV failures in combination with
failure modes trapping fuel could potentially
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Date
increase the quantity of unusable fuel on
aircraft possibly leading to fuel starvation
which could result in engine in-flight shut
down and would constitute an unsafe
condition.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
October 14, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 14, 2009.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on April 29, 2009 (74 FR
19464). That NPRM proposed to correct
E:\FR\FM\09SER1.SGM
09SER1
Agencies
[Federal Register Volume 74, Number 173 (Wednesday, September 9, 2009)]
[Rules and Regulations]
[Pages 46319-46322]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-20840]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0563; Directorate Identifier 2008-NM-180-AD;
Amendment 39-16005; AD 2009-18-09]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. This 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:
A recent design review has been carried out on the F28 Mark
0070/0100 fuel system in accordance with the guidelines related to
FAA SFAR 88 [Special Federal Aviation Regulation No. 88] (Fuel Tank
Safety Program) and JAA [Joint Aviation Authorities] INT/POL/25/12.
The review revealed that under certain failure conditions, prolonged
dry running of the fuel transfer pumps may result in an ignition
source in the centre wing fuel tank. This condition, if not
corrected, could lead to ignition of flammable fuel vapors,
resulting in fuel tank explosion and consequent loss of the
aircraft.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective October 14, 2009.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 14,
2009.
On October 27, 1999 (64 FR 51202, September 22, 1999), the Director
of the Federal Register approved the incorporation by reference of
certain other publications listed in this AD.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on June 19, 2009 (74 FR
29144), and proposed to supersede AD 99-20-01, Amendment 39-11329 (64
FR 51202, September 22, 1999). That NPRM proposed to correct an unsafe
condition for the specified products. The MCAI states:
A recent design review has been carried out on the F28 Mark
0070/0100 fuel system in accordance with the guidelines related to
FAA SFAR 88 [Special Federal Aviation Regulation No. 88] (Fuel Tank
Safety Program) and JAA [Joint Aviation Authorities] INT/POL/25/12.
The review revealed that under certain failure conditions, prolonged
dry running of the fuel transfer pumps may result in an ignition
source in the centre wing fuel tank. This condition, if not
corrected, could lead to ignition of flammable fuel vapors,
resulting in fuel tank explosion and consequent loss of the
aircraft.
To address and correct this unsafe condition, new software
(version V13.55) has been developed for the Flight Warning Computer
(FWC). This software update introduces a decreased time delay of the
centre wing fuel tank low pressure alert from 15 minutes to 60
seconds, to stop prolonged dry running of the fuel transfer pumps.
For the reasons described above, this EASA Airworthiness
Directive (AD) requires the replacement of the FWC with a modified
unit, incorporating software version V13.55.
The corrective actions include revising the airplane flight manual
(AFM) to change certain indications and warnings; installing new
software for the multifunction display unit (MFDU); and installing a
new resistor in the thrust reverser indicator and control system, or an
improved thrust reverser unlock indication relay. You may obtain
further information by examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a note within the AD.
[[Page 46320]]
Costs of Compliance
We estimate that this AD affects about 4 products of U.S. registry.
The actions that are required by AD 99-20-01 and retained in this
AD take about 7 work-hours per product, at an average labor rate of $80
per work hour. Required parts cost about $1,593 per product. Based on
these figures, the estimated cost of the currently required actions is
$2,153 per product.
We estimate that it takes about 7 work-hours per product to comply
with the new basic requirements of this AD. The average labor rate is
$80 per work-hour. Required parts cost about $5,350 per product. Where
the service information lists required parts costs that are covered
under warranty, we have assumed that there will be no charge for these
costs. As we do not control warranty coverage for affected parties,
some parties may incur costs higher than estimated here. Based on these
figures, we estimate the cost of this AD to U.S. operators to be
$23,640, or $5,910 per product.
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 AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD:
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 AD and placed it in the AD docket.
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 the NPRM, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-11329 (64 FR
51202, September 22, 1999) and adding the following new AD:
2009-18-09 Fokker Services B.V.: Amendment 39-16005. Docket No. FAA-
2009-0563; Directorate Identifier 2008-NM-180-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective October
14, 2009.
Affected ADs
(b) This AD supersedes AD 99-20-01, Amendment 39-11329.
Applicability
(c) This AD applies to airplanes, certificated in any category,
as identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) Fokker Model F.28 Mark 0100 airplanes, all serial numbers.
(2) Fokker Model F.28 Mark 0070 airplanes, serial numbers 11521,
11528 through 11537 inclusive, 11545, 11547, 11553, 11557, 11561,
11562, 11566, 11567, 11571, 11572, 11576 through 11579 inclusive,
and 11581 through 11583 inclusive. All airplanes with these serial
numbers are fitted with center wing fuel tanks.
Subject
(d) Air Transport Association (ATA) of America Codes 31 and 78:
Instruments and Engine Exhaust, respectively.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
A recent design review has been carried out on the F28 Mark
0070/0100 fuel system in accordance with the guidelines related to
FAA SFAR 88 [Special Federal Aviation Regulation No. 88] (Fuel Tank
Safety Program) and JAA [Joint Aviation Authorities] INT/POL/25/12.
The review revealed that under certain failure conditions, prolonged
dry running of the fuel transfer pumps may result in an ignition
source in the centre wing fuel tank. This condition, if not
corrected, could lead to ignition of flammable fuel vapors,
resulting in fuel tank explosion and consequent loss of the
aircraft.
To address and correct this unsafe condition, new software
(version V13.55) has been developed for the Flight Warning Computer
(FWC). This software update introduces a decreased time delay of the
centre wing fuel tank low pressure alert from 15 minutes to 60
seconds, to stop prolonged dry running of the fuel transfer pumps.
For the reasons described above, this EASA Airworthiness
Directive (AD) requires the replacement of the FWC with a modified
unit, incorporating software version V13.55.
The corrective actions include revising the airplane flight
manual (AFM) to change certain indications and warnings; installing
new software for the multifunction display unit (MFDU); and
installing a new resistor in the thrust reverser indicator and
control system, or an improved thrust reverser unlock indication
relay.
Restatement of Requirements of AD 99-20-01 With No Changes to the
Modifications
(f) Unless already done, within 18 months after October 27, 1999
(the effective date of AD 99-20-01), modify the electrical wiring of
the FWC in accordance with Part 1 or 2, as applicable, of the
Accomplishment Instructions of Fokker Service Bulletin SBF100-31-
047, Revision 1, dated March 21, 1997.
Note 1: It is not necessary to install computer software version
V10.40 into the FWC, since a later version is available and is
required to be installed by AD 99-20-01.
(g) Unless already done, concurrently with the accomplishment of
the requirements of paragraph (f) of this AD, install upgraded
computer software version V11.45 into the FWC in accordance with
Fokker Service Bulletin SBF100-31-051, dated August 15, 1998.
Note 2: AlliedSignal Grimes Aerospace has issued Service
Bulletin 80-0610-31-0031, dated May 14, 1998, as an additional
source
[[Page 46321]]
of guidance for installation of the upgraded computer software
version into the FWC.
Note 3: Operators should note that Fokker Service Bulletin
SBF100-31-051, dated August 15, 1998, specifies prior or concurrent
accomplishment of Fokker Service Bulletin SBF100-78-014 (which
specifies concurrent accomplishment of Fokker Component Service
Bulletin (CSB) P41440-78-04, and prior or concurrent accomplishment
of Fokker Service Bulletin SBF100-78-012 and CSB P41440-78-05).
Related FAA AD 99-20-02, amendment 39-11330, requires accomplishment
of these four other service bulletins.
New Requirements of This AD: Actions and Compliance
(h) Unless already done, do the following actions.
(1) Within 36 months after the effective date of this AD,
replace FWC units having part number (P/N) 80-0610-3-45 and P/N 80-
0610-3-50 with modified units having P/N 80-0610-3-55, in accordance
with the Accomplishment Instructions of Fokker Service Bulletin
SBF100-31-067, Revision 1, dated April 24, 2008.
(2) Within 36 months after the effective date of this AD and
concurrently with the accomplishment of paragraph (h)(1) of this AD,
revise the Emergency and Abnormal Procedures sections of the
airplane flight manual (AFM), as specified in Fokker Manual Change
Notification-Operational Documentation MCNO-F100-050, dated January
31, 2008, which is included in Fokker Service Bulletin SBF100-31-
067, Revision 1, dated April 24, 2008. These AFM sections provide
alterations, which are introduced in Fokker Service Bulletin SBF100-
31-067, Revision 1, dated April 24, 2008.
Note 4: Revisions to the Emergency Procedures and Abnormal
Procedures sections of the AFM, as specified in Fokker MCNO-F100-
050, dated January 31, 2008, may be done by inserting copies of
Fokker MCNO-F100-050, dated January 31, 2008, into the AFM. When the
information in Fokker MCNO-F100-050, dated January 31, 2008, has
been included in general revisions of the AFM, the general revisions
may be inserted in the AFM, provided the relevant information in the
general revisions are identical to that in Fokker MCNO-F100-050,
dated January 31, 2008.
(3) After accomplishing paragraph (h)(1) of this AD, no person
may install an FWC having P/N 80-0610-3-45 or P/N 80-0610-3-50,
unless it has been modified to P/N 80-0610-3-55 standard in
accordance with Honeywell Service Bulletin 80-0610-31-0003, dated
February 13, 2008.
(4) Within 36 months after the effective date of this AD,
install software version V12 for the MFDU in accordance with the
Accomplishment Instructions of Fokker Service Bulletin SBF100-31-
060, dated June 1, 2002.
(5) Within 36 months after the effective date of this AD, modify
the thrust reverser indication and control system in accordance with
the Accomplishment Instructions of Fokker Service Bulletin SBF100-
78-016, dated October 1, 1999; or modify the thrust reverser unlock
indication relay in accordance with the Accomplishment Instructions
of Fokker Service Bulletin SBF100-78-017, dated December 1, 1999.
FAA AD Differences
Note 5: This AD differs from the MCAI and/or service information
as follows:
(1) Replacing the MFDU in accordance with Fokker Service
Bulletin SBF100-31-060, dated June 1, 2002, is not included in the
MCAI; however, this AD includes that action. It is necessary to
install a new version of the MFDU software before installing the new
version of the FWC software.
(2) Modifying the thrust reverser indication and control system
in accordance with Fokker Service Bulletin SBF100-78-016, dated
October 1, 1999; or modifying the thrust reverser unlock indication
relay in accordance with Fokker Service Bulletin SBF100-78-017,
dated December 1, 1999, is not included in the MCAI; however, this
AD includes those actions. It is necessary to do one of those
actions before installing the MFDU software.
Other FAA AD Provisions
(i) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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: 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.
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
(j) Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2008-0090, dated May 13, 2008, and the service information
identified in Table 1 of this AD, for related information.
Table 1--Related Information
----------------------------------------------------------------------------------------------------------------
Service information-- Revision level-- Dated--
----------------------------------------------------------------------------------------------------------------
Fokker Service Bulletin SBF100-31-047... 1.......................... March 21, 1997.
Fokker Service Bulletin SBF100-31-051... Original................... August 15, 1998.
Fokker Service Bulletin SBF100-31-060... Original................... June 1, 2002.
Fokker Service Bulletin SBF100-31-067, 1.......................... April 24, 2008.
including Fokker Manual Change
Notification-Operational Documentation
MCNO-F100-50, dated January 31, 2008.
Fokker Service Bulletin SBF100-78-016... Original................... October 1, 1999.
Fokker Service Bulletin SBF100-78-017... Original................... December 1, 1999.
----------------------------------------------------------------------------------------------------------------
Material Incorporated by Reference
(k) You must use the service information contained in Table 2 of
this AD to do the actions required by this AD, unless the AD
specifies otherwise.
Table 2--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Fokker Service Bulletin SBF100-31-047... 1.......................... March 21, 1997.
Fokker Service Bulletin SBF100-31-051... Original................... August 15, 1998.
[[Page 46322]]
Fokker Service Bulletin SBF100-31-060... Original................... June 1, 2002.
Fokker Service Bulletin SBF100-31-067, 1.......................... April 24, 2008.
including Fokker Manual Change
Notification-Operational Documentation
MCNO-F100-50, dated January 31, 2008.
Fokker Service Bulletin SBF100-78-016... Original................... October 1, 1999.
Fokker Service Bulletin SBF100-78-017... Original................... December 1, 1999.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of the service information contained in
Table 3 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.
Table 3--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Fokker Service Bulletin SBF100-31-060... Original................... June 1, 2002.
Fokker Service Bulletin SBF100-31-067, 1.......................... April 24, 2008.
including Fokker Manual Change
Notification-Operational Documentation
MCNO-F100-50, dated January 31, 2008.
Fokker Service Bulletin SBF100-78-016... Original................... October 1, 1999.
Fokker Service Bulletin SBF100-78-017... Original................... December 1, 1999.
----------------------------------------------------------------------------------------------------------------
(2) The Director of the Federal Register previously approved
the incorporation by reference of Fokker Service Bulletin SBF100-31-
047, Revision 1, dated March 21, 1997; and Fokker Service Bulletin
SBF100-31-051, dated August 15, 1998; on October 27, 1999 (64 FR
51202, September 22, 1999).
(3) For Fokker service information identified in this 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.
(4) For AlliedSignal Grimes Aerospace and Honeywell service
information identified in this AD, contact Honeywell Aerospace,
Technical Publications and Distribution, M/S 2101-201, P.O. Box
52170, Phoenix, Arizona 85072-2170; telephone 602-365-5535; fax 602-
365-5577; Internet https://www.honeywell.com.
(5) You may review copies of the 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.
(6) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on August 18, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-20840 Filed 9-8-09; 8:45 am]
BILLING CODE 4910-13-P