[Federal Register: May 9, 2005 (Volume 70, Number 88)]
[Proposed Rules]
[Page 24326-24330]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09my05-16]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
[[Page 24326]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21137; Directorate Identifier 2002-NM-86-AD]
RIN 2120-AA64
Airworthiness Directives; BAE Systems (Operations) Limited
(Jetstream) Model 4101 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all BAE Systems (Operations) Limited (Jetstream) Model 4101
airplanes. This proposed AD would require repetitive detailed and
specialized inspections to detect fatigue damage in the fuselage,
replacement of certain bolt assemblies, and corrective actions if
necessary. This proposed AD is prompted by a review of primary airframe
fatigue test results and Maintenance Steering Group 3 (MSG-3) analysis.
We are proposing this AD to detect and correct fatigue damage of the
fuselage, door, engine nacelle, empennage, and wing structures, which
could result in reduced structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by June 8, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
By fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
British Aerospace Regional Aircraft American Support, 13850 Mclearen
Road, Herndon, Virginia 20171.
You can examine the contents of this AD docket on the Internet at
http://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401,
on the plaza level of the Nassif Building, Washington, DC. The docket
number is FAA-2005-21137; the directorate identifier for this docket is
2002-NM-86-AD.
FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1175; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-21137;
Directorate Identifier 2002-NM-86-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments submitted by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of our
docket website, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You can review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit http://dms.dot.gov.
Examining the Docket
You can examine the AD docket on the Internet at http://dms.dot.gov
, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the DMS receives them.
Discussion
The Civil Aviation Authority (CAA), which is the airworthiness
authority for the United Kingdom, notified us that an unsafe condition
may exist on all BAE Systems (Operations) Limited (Jetstream) Model
4101 airplanes. The CAA advises that, following an extensive review of
the primary airframe fatigue test results and Maintenance Steering
Group 3 (MSG-3) analysis for the Model 4101 airplanes, new areas and
thresholds of fatigue damage were identified. New inspections and
revisions to existing inspections for fatigue damage (requirements and
inspection thresholds in particular) are needed to address the
findings. These inspections are necessary to maintain the structural
integrity of the airplane. Fatigue damage of the fuselage, door, engine
nacelle, empennage, and wing structures, if not detected and corrected
in a timely manner, could result in reduced structural integrity of the
airplane.
Relevant Service Information
BAE Systems (Operations) Limited has issued Service Bulletin J41-
51-001, Revision 2, dated April 30, 2003. The service bulletin
describes procedures for repetitive detailed and specialized
inspections of the fuselage to detect fatigue damage, replacement of
the bolt assemblies of the pintle bearing housing and upper club foot
fitting with new bolt assemblies, and corrective actions if necessary.
The specialized inspections include eddy current inspections (including
high frequency and rotating), radiographic inspections, a magnetic
particle inspection, and a torque measurement. The areas to be
inspected
[[Page 24327]]
are located in or around door, fuselage, engine nacelle, empennage, and
wing structures. In addition, the service bulletins specify submitting
inspection reports after most of the inspection procedures are
completed. The corrective actions include replacing a damaged part with
a new part, and repairing damage in accordance with the service
bulletin, or in accordance with a method approved by BAE Systems
(Operations) Limited if damage is outside specified limits.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The CAA mandated
the service information and issued British airworthiness directive 005-
02-2002 to ensure the continued airworthiness of these airplanes in the
United Kingdom.
FAA's Determination and Requirements of the Proposed AD
This airplane model is manufactured in the United Kingdom and is
type certificated for operation in the United States under the
provisions of Sec. 21.29 of the Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral airworthiness agreement. Pursuant
to this bilateral airworthiness agreement, the CAA has kept the FAA
informed of the situation described above. We have examined the CAA's
findings, evaluated all pertinent information, and determined that we
need to issue an AD for products of this type design that are
certificated for operation in the United States.
Therefore, we are proposing this AD, which would require
accomplishing the actions specified in the service information
described previously, except as discussed under ``Differences Between
the Proposed AD and the Service Bulletin.''
Differences Between the Proposed AD and the Service Bulletin
Operators should note that, although the Accomplishment
Instructions of the referenced service bulletin describes procedures
for submitting inspection reports, this proposed AD would not require
those actions. We do not need this information from operators.
The service bulletin specifies that you may contact the
manufacturer for instructions on how to repair certain conditions, but
this proposed AD would require you to repair those conditions using a
method that we or the CAA (or its delegated agent) approve. In light of
the type of repair that would be required to address the unsafe
condition, and consistent with existing bilateral airworthiness
agreements, we have determined that, for this proposed AD, a repair we
or the CAA approve would be acceptable for compliance with this
proposed AD.
Grace Period
Operators should note that, although the service bulletin does not
list a grace period in the compliance times for some of the actions,
this proposed AD adds a grace period to the compliance times. We find
that a grace period will keep airplanes from being grounded
unnecessarily.
Also, although the service bulletin specifies a grace period for
some actions, this proposed AD has a different grace period. We find
that this modified grace period will keep airplanes from being grounded
unnecessarily.
Clarification of Flight Cycle Terminology
Operators should note that, although the Accomplishment
Instructions of the referenced service bulletins use ``flights'' to
define some compliance times, this proposed AD uses ``total flight
cycles.''
Clarification of Inspection Terminology
In this proposed AD, the ``detailed visual inspection,'' ``detailed
internal visual inspection,'' ``detailed internal inspection,'' and
``detailed external visual inspection'' specified in the service
bulletin are referred to as a ``detailed inspection.'' We have included
the definition for a detailed inspection in Note 1 of the proposed AD.
Clarification of Initial Inspection Threshold
For airplanes not inspected previously, the service bulletin
specifies inspection thresholds of 8 years and 4 years after first
flight. However, for these same airplanes, paragraph (g) of this
proposed AD specifies an inspection threshold of 96 months (8 years)
and 48 months (4 years), as applicable, after the date of issuance of
the original standard Airworthiness Certificate or the date of issuance
of the original Export Certificate of Airworthiness. This decision is
based on our determination that ``first flight'' may be interpreted
differently by different operators. We find that our proposed
terminology is generally understood within the industry and records
will always exist that establish these dates with certainty.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Cost per
Work Average labor airplane, per Number of U.S.-
Action hours rate per hour Parts inspection registered Fleet cost
cycle airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections of the door structure...... 17 $65 None...................... $1,105 57 Up to $62,985, per
inspection cycle.
Inspections of the fuselage structure.. 164 65 None...................... 10,660 57 Up to $607,620, per
inspection/replacement
cycle.
Inspections of the engine nacelle 4 65 None...................... 260 57 Up to $14,820, per
structure. inspection cycle.
Inspections of the empennage structure. 14 65 None...................... 910 57 Up to $51,870, per
inspection cycle.
Inspections of the wing structure...... 24 65 None...................... 1,560 57 Up to $88,920, per
inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
The total proposed actions would take about 223 work hours per
airplane, at an average labor rate of $65 per work hour. Based on these
figures, the estimated cost of the total proposed AD for U.S. operators
is up to $826,215, or $14,495 per airplane, per inspection cycle.
[[Page 24328]]
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
BAE Systems (Operations) Limited (Formerly British Aerospace
Regional Aircraft): Docket No. FAA-2005-21137; Directorate
Identifier 2002-NM-86-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by June 8, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all BAE Systems (Operations) Limited
Model Jetstream 4101 airplanes, certificated in any category.
Unsafe Condition
(d) This AD was prompted by a review of primary airframe fatigue
test results and Maintenance Steering Group 3 (MSG-3) analysis. We
are issuing this AD to detect and correct fatigue damage of the
fuselage, door, engine nacelle, empennage, and wing structures,
which could result in reduced structural integrity of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Service Bulletin Reference
(f) The term ``the service bulletin,'' as used in this AD, means
BAE Systems (Operations) Limited Service Bulletin J41-51-001,
Revision 2, dated April 30, 2003.
Inspection and Corrective Actions
(g) At the compliance times specified in the ``Initial
Compliance Time'' column of Tables 1, 2, 3, 4, and 5 of this AD: Do
the applicable detailed inspections and specialized inspections to
detect fatigue damage, and replacement of certain bolt assemblies,
and any applicable corrective actions, in accordance with the
Accomplishment Instructions of the service bulletin. Do any
corrective action before further flight. Repeat the inspections and
replacement thereafter at intervals specified in the ``Repetitive
Intervals'' column of Tables 1, 2, 3, 4, and 5 of this AD.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirrors, magnifying lenses, etc. may be necessary. Surface cleaning
and elaborate procedures may be required.''
Table 1.--Appendix 1 Compliance Times
----------------------------------------------------------------------------------------------------------------
Initial compliance time (whichever occurs later
Part of actions between the times in ``inspection threshold'' and
specified in appendix 1 of the ``grace period'') Repetitive intervals
service bulletin -----------------------------------------------------
Inspection threshold Grace period
----------------------------------------------------------------------------------------------------------------
1, 6............................. Before the accumulation Within 500 flight cycles At intervals not to
of 22,500 total flight after the effective exceed 3,300 flight
cycles and after the date of this AD. cycles.
accumulation of 20,000
total flight cycles.
2................................ Before the accumulation Within 500 flight cycles At intervals not to
of 20,000 total flight after the effective exceed 5,200 flight
cycles. date of this AD. cycles.
3, 5, 7.......................... Before the accumulation Within 500 flight cycles At intervals not to
of 21,000 total flight after the effective exceed 10,000 flight
cycles. date of this AD. cycles.
4................................ Before the accumulation Within 500 flight cycles At intervals not to
of 26,000 total flight after the effective exceed 26,000 flight
cycles and after the date of this AD. cycles.
accumulation of 20,000
total flight cycles.
----------------------------------------------------------------------------------------------------------------
[[Page 24329]]
Table 2.--Appendix 2 Compliance Times
----------------------------------------------------------------------------------------------------------------
Initial compliance time (whichever occurs later
between the times in ``inspection/replacement
Part of actions threshold'' and ``grace period'')
specified in appendix 2 of the ----------------------------------------------------- Repetitive intervals
service bulletin Inspection/replacement
threshold Grace period
----------------------------------------------------------------------------------------------------------------
1, 3, 32......................... Within 96 months after 12 months after the At intervals not to
the date of issuance of effective date of this exceed 24 months.
the original standard AD.
Airworthiness
Certificate or the date
of issuance of the
original Export
Certificate of
Airworthiness, whichever
occurs later.
2................................ Before the accumulation Within 500 flight cycles At intervals not to
of 23,000 total flight after the effective exceed 10,000 flight
cycles. date of this AD. cycles.
4, 10, 11, 12, 13................ Before the accumulation Within 500 flight cycles At intervals not to
of 20,000 total flight after the effective exceed 6,600 flight
cycles. date of this AD. cycles.
5................................ Within 48 months after 12 months after the At intervals not to
the date of issuance of effective date of this exceed 24 months.
the original standard AD.
Airworthiness
Certificate or the date
of issuance of the
original Export
Certificate of
Airworthiness, whichever
occurs later.
6................................ Before the accumulation Within 500 flight cycles At intervals not to
of 20,000 total flight after the effective exceed 5,400 flight
cycles. date of this AD. cycles.
7................................ Before the accumulation Within 500 flight cycles At intervals not to
of 22,400 total flight after the effective exceed 8,200 flight
cycles and after the date of this AD. cycles.
accumulation of 20,000
total flight cycles.
8................................ Before the accumulation Within 500 flight cycles At intervals not to
of 19,000 total flight after the effective exceed 8,200 flight
cycles. date of this AD. cycles.
9................................ Before the accumulation Within 500 flight cycles At intervals not to
of 23,000 total flight after the effective exceed 23,000 flight
cycles. date of this AD. cycles.
14............................... Before the accumulation Within 500 flight cycles At intervals not to
of 19,700 total flight after the effective exceed 4,700 flight
cycles. date of this AD. cycles.
15............................... Before the accumulation Within 500 flight cycles At intervals not to
of 25,000 total flight after the effective exceed 13,600 flight
cycles and after the date of this AD. cycles.
accumulation of 20,000
total flight cycles.
16, 19, 20....................... Before the accumulation Within 500 flight cycles At intervals not to
of 26,000 total flight after the effective exceed 25,800 flight
cycles and after the date of this AD. cycles.
accumulation of 20,000
total flight cycles.
17, 21, 29, 30................... Before the accumulation Within 500 flight cycles At intervals not to
of 26,000 total flight after the effective exceed 30,000 flight
cycles and after the date of this AD. cycles.
accumulation of 20,000
total flight cycles.
18............................... Before the accumulation Within 500 flight cycles At intervals not to
of 26,000 total flight after the effective exceed 33,000 flight
cycles and after the date of this AD. cycles.
accumulation of 20,000
total flight cycles.
22............................... Before the accumulation Within 500 flight cycles At intervals not to
of 26,000 total flight after the effective exceed 16,500 flight
cycles and after the date of this AD. cycles.
accumulation of 20,000
total flight cycles.
23............................... Before the accumulation Within 500 flight cycles At intervals not to
of 22,000 total flight after the effective exceed 7,400 flight
cycles and after the date of this AD. cycles.
accumulation of 20,000
total flight cycles.
24............................... Before the accumulation Within 500 flight cycles At intervals not to
of 23,600 total flight after the effective exceed 15,700 flight
cycles and after the date of this AD. cycles.
accumulation of 20,000
total flight cycles.
25............................... Before the accumulation Within 500 flight cycles At intervals not to
of 26,000 total flight after the effective exceed 12,700 flight
cycles and after the date of this AD. cycles.
accumulation of 20,000
total flight cycles.
26............................... Before the accumulation Within 500 flight cycles At intervals not to
of 26,000 total flight after the effective exceed the 21,800
cycles and after the date of this AD. flight cycles.
accumulation of 20,000
total flight cycles.
27............................... Before the accumulation Within 500 flight cycles At intervals not to
of 26,000 total flight after the effective exceed 18,300 flight
cycles and after the date of this AD. cycles.
accumulation of 20,000
total flight cycles.
28............................... Between 20,000 and 26,000 Within 500 flight cycles At intervals not to
total flight cycles. after the effective exceed 9,500 flight
date of this AD. cycles.
31............................... Before the accumulation Within 500 flight cycles At intervals not to
of 26,000 total flight after the effective exceed 16,300 flight
cycles and after the date of this AD. cycles.
accumulation of 20,000
total flight cycles.
33............................... Before the accumulation Within 500 flight cycles At intervals not to
of 26,000 total flight after the effective exceed 26,000 flight
cycles. date of this AD. cycles.
----------------------------------------------------------------------------------------------------------------
[[Page 24330]]
Table 3.--Appendix 3 Compliance Times
----------------------------------------------------------------------------------------------------------------
Initial compliance time (whichever occurs later
Part of actions between the times in ``inspection threshold'' and
specified in appendix 3 of the ``grace period'') Repetitive intervals
service bulletin --------------------------------------------------------
Inspection threshold Grace period
----------------------------------------------------------------------------------------------------------------
1, 2.............................. Before the accumulation of Within 500 flight cycles At intervals not to
24,000 total flight after the effective date exceed 11,000
cycles and after the of this AD. flight cycles.
accumulation of 20,000
total flight cycles.
----------------------------------------------------------------------------------------------------------------
Table 4.--Appendix 4 Compliance Times
----------------------------------------------------------------------------------------------------------------
Initial Compliance time (whichever occurs later
Part of actions between the times in ``inspection threshold'' and
specified in appendix 4 of the ``grace period'') Repetitive intervals
service bulletin --------------------------------------------------------
Inspection threshold Grace period
----------------------------------------------------------------------------------------------------------------
1................................. Before the accumulation of Within 500 flight cycles At intervals not to
26,000 total flight after the effective date exceed 12,000
cycles and after the of this AD. flight cycles.
accumulation of 20,000
total flight cycles.
2................................. Before the accumulation of Within 500 flight cycles At intervals not to
26,000 total flight after the effective date exceed 30,000
cycles and after the of this AD. flight cycles.
accumulation of 20,000
total flight cycles.
3, 5.............................. Within 48 months after the 12 months after the At intervals not to
date of issuance of the effective date of this AD. exceed 48 months.
original standard
Airworthiness Certificate
or the date of issuance
of the original Export
Certificate of
Airworthiness, whichever
occurs later.
4, 6.............................. 96 months after the date 12 months after the At intervals not to
of issuance of the effective date of this AD. exceed 48 months.
original standard
Airworthiness Certificate
or the date of issuance
of the original Export
certificate of
Airworthiness, whichever
occurs later.
----------------------------------------------------------------------------------------------------------------
Table 5.--Appendix 5 Compliance Times
----------------------------------------------------------------------------------------------------------------
Initial compliance time (whichever occurs later
Part of actions between the times in ``inspection threshold'' and
specified in appendix 5 of the ``grace period'') Repetitive intervals
service bulletin --------------------------------------------------------
Inspection threshold Grace period
----------------------------------------------------------------------------------------------------------------
1, 7.............................. Before the accumulation of Within 500 flight cycles At intervals not to
26,000 total flight after the effective date exceed 30,000
cycles and after the of this AD. flight cycles.
accumulation of 20,000
total flight cycles.
2, 5, 6........................... Before the accumulation of Within 500 flight cycles At intervals not to
26,000 total flight after the effective date exceed 9,000 flight
cycles and after the of this AD. cycles.
accumulation of 20,000
total flight cycles.
3, 4.............................. Before the accumulation of Within 500 flight cycles At intervals not to
26,000 total flight after the effective date exceed 7,900 flight
cycles and after the of this AD. cycles.
accumulation 20,000 total
flight cycles.
----------------------------------------------------------------------------------------------------------------
Repairs for Damage Beyond Service Bulletin Limits
(h) If any fatigue damage is found that exceeds the limits
specified in the service bulletin: Before further flight, repair the
damage according to a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate;
or the Civil Aviation Authority (or its delegated agent).
Previous Actions
(i) Actions done before the effective date of this AD in
accordance with BAE Systems (Operations) Limited Service Bulletin
J41-51-001, dated February 15, 2002; and Revision 1, dated August 7,
2002, are acceptable for compliance with the requirements of
paragraphs (g) and (h) of this AD.
No Report Required
(j) Although the service bulletin referenced in this AD
specifies to submit certain information to the manufacturer, this AD
does not include that requirement.
Alternative Methods of Compliance (AMOCs)
(k) The Manager, International Branch, ANM-116, FAA, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
Related Information
(l) British airworthiness directive 005-02-2002 also addresses
the subject of this AD.
Issued in Renton, Washington, on April 29, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-9185 Filed 5-6-05; 8:45 am]
BILLING CODE 4910-13-P