[Federal Register: April 9, 2009 (Volume 74, Number 67)]
[Proposed Rules]
[Page 16152-16154]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09ap09-15]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0324; Directorate Identifier 2008-NM-186-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B4-601, B4-603, B4-
605R, B4-620, B4-622, B4-622R, F4-605R, F4-622R, and C4-605R Variant F
Series Airplanes Equipped With Simmonds Precision Products, Inc., Fuel
Quantity Indicating System Sensors and In-Tank Harnesses Installed in
Accordance With Supplemental Type Certificate (STC) ST00092BO
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Airbus model series airplanes. This proposed AD would require
revising the Airworthiness Limitations Section of the Instructions for
Continuing Airworthiness to incorporate new fuel system limitations for
airplanes modified in accordance with STC ST00092BO. This AD also
requires performing a general visual inspection for tank unit
separation and compensator separation of the: center, inner, outer fuel
tanks, and trim fuel tanks of the tank units, and corrective actions if
necessary. This proposed AD results from fuel system reviews conducted
by the manufacturer. We are proposing this AD to prevent a potential of
ignition sources inside fuel tanks, which in combination with flammable
fuel vapors, could result in a fuel tank fire or explosion and
consequent loss of the airplane.
DATES: We must receive comments on this proposed AD by May 26, 2009.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://
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 Goodrich
Corporation, Fuel and Utility Systems, 100 Panton Road, Vergennes,
Vermont 05491-1008; telephone 802-877-4476; e-mail
lgd.TechPubs.Oakville@goodrich.com; Internet http://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.
Examining the AD Docket
You may examine the AD docket on the Internet at http://
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: Marc Ronell, Aerospace Engineer, ANE-
150, FAA, Boston Aircraft Certification Office, 12 New England
Executive Park, Burlington, Massachusetts 01803; telephone (781) 238-
7776; fax (781) 238-7170.
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-2009-0324;
Directorate Identifier 2008-NM-186-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 http://
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 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.
Relevant Service Information
We have reviewed Goodrich A300-600 Instructions for Continued
Airworthiness, Document T3012-0005-0101, Revision B, dated June 12,
2008. The document describes new airworthiness limitations (AWLs) for
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fuel tank systems. The new AWLs include:
AWL inspections, which are periodic inspections of certain
features for latent failures that could contribute to an ignition
source; and
Critical design configuration control limitations (CDCCL),
which are limitation requirements to preserve a critical ignition
source prevention feature of the fuel tank system design that is
necessary to prevent the occurrence of an unsafe condition. The purpose
of a CDCCL is to provide instruction to retain the critical ignition
source prevention feature during configuration changes that may be
caused by alterations, repairs, or maintenance actions. A CDCCL is not
a periodic inspection.
The instructions describe procedures to perform a general visual
inspection (GVI) for tank unit separation and compensator separation of
the: Center, inner, outer fuel tanks, and trim fuel tanks of the tank
units.
We have also reviewed Goodrich Service Bulletin 300723-0101-28-01,
Revision 1, dated July 1, 2004. The service bulletin describes
procedures to perform an inspection of each probe and compensator
location for sufficient clearance to structure.
Other Related AD
We issued AD 2004-05-05, amendment 39-13499 (69 FR 10319, March 5,
2004) on February 20, 2004, for certain Airbus Model A300-600, A300,
and A310 airplanes. We issued that AD to require a one-time inspection
of the space between the fuel quantity indication probes and any
adjacent structures for minimum clearance and corrective action if
necessary.
Doing inspections in accordance with section 2.2.3 of the Goodrich
A300-600 Instructions for Continued Airworthiness, Document T3012-0005-
0101, Revision B, dated June 12, 2008, and Goodrich Service Bulletin
300723-0101-28-01, Revision 1, dated July 1, 2004, are acceptable
methods of compliance for paragraphs (b) and (c) of AD 2004-05-05.
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(se) same type
design(s). This proposed AD would require accomplishing the actions
specified in the service information described previously, except as
described in the ``Differences Between the Proposed AD and the Service
Information.''
Differences Between the Proposed AD and the Service Information
The service information does not specify initial compliance times
for doing GVI for tank unit separation and compensator separation of
the: center, inner, outer fuel tanks, and trim fuel tanks of the tank
units. This AD requires an initial inspection for the GVI inspections
within six months after the effective date of this AD.
The service information does not include corrective actions if
incorrect separation is found. This AD also requires, if incorrect
separation is found, correction of the separation in accordance with
the airplane maintenance manual for the corresponding inspection
specified in section 2.2.3 of the Goodrich A300-600 Instructions for
Continued Airworthiness, Document T3012-0005-0101, Revision B, dated
June 12, 2008.
Costs of Compliance
We estimate that this proposed AD would affect 68 airplanes of U.S.
registry. We also estimate that it would take about 8 work-hours per
product to comply with this proposed AD. The average labor rate is $80
per work-hour. Based on these figures, we estimate the cost of this
proposed AD to the U.S. operators to be $43,520, or $640 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 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:
Simmonds Precision Products, Inc., D/B/A Goodrich Corporation Fuel &
Utility Systems: Docket No. FAA-2009-0324; Directorate Identifier
2008-NM-186-AD.
Comments Due Date
(a) We must receive comments by May 26, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-
605R, B4-620, B4-622, B4-622R, F4-605R, F4-622R, and C4-605R Variant
F series airplanes, certificated in any category, equipped with
Simmonds Precision Products, Inc., Fuel Quantity Indicating System
sensors and in-tank harnesses installed in accordance with
supplemental type certificate (STC) ST00092BO.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new inspections and critical design
configuration control limitations (CDCCLs). Compliance with these
inspections is required by 14 CFR 91.403(c). For airplanes that have
been previously modified, altered,
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or repaired in the areas addressed by these inspections and CDCCLs,
the operator may not be able to accomplish the inspections and
CDCCLs, 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 according to paragraph (o) of this
AD. The request should include a description of changes to the
required inspections and CDCCLs 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. The Federal Aviation Administration is issuing this AD
to reduce the potential of ignition sources inside fuel tanks, which
in combination with flammable fuel vapors, could result in fuel tank
fire or explosions and consequent loss of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless already
done.
Revision to the Airworthiness Limitations Section
(g) Within 30 days after the effective date of this AD, revise
the Airworthiness Limitations Section (ALS) of the Instructions for
Continued Airworthiness to incorporate the inspections specified in
section 2.2.3 of the Goodrich A300-600 Instructions for Continued
Airworthiness, Document T3012-0005-0101, Revision B, dated June 12,
2008.
(h) Within six months after the effective date of this AD, do a
general visual inspection for tank unit separation and compensator
separation of the: center, inner, outer fuel tanks, and trim fuel
tanks of the tank units, in accordance with section 2.2.3 of the
Goodrich A300-600 Instructions for Continued Airworthiness, Document
T3012-0005-0101, Revision B, dated June 12, 2008. If incorrect
separation is found, in accordance with section 2.2.3 of the
Goodrich A300-600 Instructions for Continued Airworthiness, Document
T3012-0005-0101, Revision B, dated June 12, 2008, before further
flight, correct the separation in accordance with the airplane
maintenance manual for the corresponding inspection specified in
section 2.2.3 of the Goodrich A300-600 Instructions for Continued
Airworthiness Document T3012-0005-0101, Revision B, dated June 12,
2008. A review of airplane maintenance records is acceptable in lieu
of this inspection if the requirement of Table 6 in section 10.1 of
the Goodrich A300-600 Instructions for Continued Airworthiness,
Document T3012-0005-0101, Revision B, dated June 12, 2008, can be
conclusively determined to have been done from that review.
(i) Within 30 days after the effective date of this AD, revise
the ALS of the Instructions for Continued Airworthiness to
incorporate the CDCCLs as defined in section 10.1 of the Goodrich
A300-600 Instructions for Continued Airworthiness, Document T3012-
0005-0101, Revision B, dated June 12, 2008.
(j) Except as provided by paragraph (o) of this AD: After
accomplishing the actions specified in paragraphs (g) and (i) of
this AD, no alternative inspection, inspection intervals, or CDCCLs
may be used.
Actions Done According to Previous Service Information
(k) Inspections are acceptable for compliance with the
requirements of paragraph (h) of this AD, if done before the
effective date of this AD, in accordance with Goodrich Service
Bulletin 300723-0101-28-01, dated April 15, 2004.
(l) Inspections are also acceptable for compliance with the
requirements of paragraph (h) of this AD, if done in accordance with
Goodrich Service Bulletin 300723-0101-28-01, Revision 1, dated July
1, 2004.
Acceptable Methods of Compliance for AD 2004-05-05
(m) Doing the inspections in section 2.2.3 of the Goodrich A300-
600 Instructions for Continued Airworthiness Document T3012-0005-
0101, Revision B, dated June 12, 2008, is considered an acceptable
method of compliance to paragraphs (b) and (c) of AD 2004-05-05,
amendment 39-13499.
(n) Doing the inspections in accordance with Goodrich Service
Bulletin 300723-0101-28-01, Revision 1, dated July 1, 2004, is an
acceptable method of compliance to paragraphs (b) and (c) of AD
2004-05-05.
Alternative Methods of Compliance (AMOCs)
(o)(1) The Manager, Boston 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: Marc Ronell, Aerospace Engineer, ANE-150, FAA, Boston ACO, 12
New England Executive Park, Burlington, Massachusetts 01803;
telephone (781) 238-7776; fax (781) 238-7170.
(2) To request a different method of compliance or a different
compliance 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 April 2, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-8081 Filed 4-8-09; 8:45 am]
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