[Federal Register: January 29, 2003 (Volume 68, Number 19)]
[Rules and Regulations]
[Page 4374-4378]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29ja03-6]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-308-AD; Amendment 39-13026; AD 2003-03-02]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 767 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to all Boeing Model 767 series airplanes, that
currently requires repetitive detailed and eddy current inspections to
detect cracks of certain midspar fuse pins, and replacement of any
cracked midspar fuse pin with a new fuse pin. This amendment reduces
certain compliance times for certain inspections, expands the detailed
and eddy current inspections, and limits the applicability in the
existing AD. This amendment also provides for optional terminating
action, which ends the repetitive inspections. The actions specified in
this AD are intended to prevent loss of the strut and engine due to
corrosion damage and cracking of both fuse pins on the same strut. This
action is intended to address the identified unsafe condition.
DATES: Effective February 13, 2003.
The incorporation by reference of a certain publication, as listed
in the regulations, is approved by the Director of the Federal Register
as of February 13, 2003.
The incorporation by reference of Boeing Alert Service Bulletin
767-54A0062, dated April 14, 1994, as listed in the regulations, was
approved previously by the Director of the Federal Register as of June
10, 1994 (59 FR 27229, May 26, 1994).
Comments for inclusion in the Rules Docket must be received on or
before March 31, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2002-NM-308-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays. Comments may be submitted via fax to (425) 227-1232.
Comments may also be sent via the Internet using the following address:
9-anm-iarcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2002-NM-308-AD'' in the subject line and need not
be submitted in triplicate. Comments sent via the Internet as attached
electronic files must be formatted in Microsoft Word 97 for Windows or
ASCII text.
The service information referenced in this AD may be obtained from
Boeing Commercial Airplane Group, PO Box 3707, Seattle, Washington
98124-2207. This information may be examined at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Suzanne Masterson, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2772; fax (425) 227-1181.
[[Page 4375]]
SUPPLEMENTARY INFORMATION: On May 18, 1994, the FAA issued AD 94-11-02,
amendment 39-8918 (59 FR 27229, June 10, 1994), applicable to all
Boeing Model 767 series airplanes, to require repetitive detailed
visual and eddy current inspections to detect cracks of certain midspar
fuse pins, and replacement of any cracked midspar fuse pin with a new
fuse pin. That action was prompted by reports of longitudinal fatigue
cracks on certain midspar fuse pins installed on Boeing Model 767
series airplanes. The actions required by that AD are intended to
prevent loss of the strut and engine due to cracking of both fuse pins
on the same strut.
Actions Since Issuance of Previous Rule
Since the issuance of AD 94-11-02, an operator has reported a
fractured outboard midspar fuse pin (part number (P/N) 311T3102-1) of
the left engine pylon, which was found during a scheduled maintenance
visit. The fuse pin also had corrosion on the pin and within the bore.
The airplane had accumulated 9,456 total flight cycles, and 38,911
total flight hours. The initial inspection for airplanes with midspar
fuse pins having P/N 311T3102-1, as required by AD 94-11-02, begins
prior to the accumulation of 15,000 total landings on the fuse pin, or
within 90 days after the effective date of the existing AD, whichever
occurs later. In light of this information, the FAA finds it necessary
to reduce the compliance time for the initial inspection for airplanes
with midspar fuse pins. This AD also includes inspecting for corrosion
of the midspar fuse pins, in addition to cracks, and limits the
applicability in the existing AD.
Explanation of Relevant Service Information
The FAA has reviewed and approved Boeing Alert Service Bulletin
767-54A0062, Revision 5, dated November 11, 2002 (Boeing Alert Service
Bulletin 767-54A0062, dated April 14, 1994, was referenced in the
existing AD for accomplishment of the actions specified). Revision 5 of
the service bulletin reduces certain compliance times, references
certain actions specified in related service bulletins that would
eliminate the need for the repetitive inspections, and clarifies
certain procedures. Revision 5 describes procedures for repetitive
detailed and eddy current inspections for cracks and corrosion of
certain midspar fuse pins, and replacement of any cracked midspar fuse
pin with a new fuse pin. The service bulletin also describes procedures
for a magnetic particle inspection to verify cracks if the fuse pins
are removed from the strut. Accomplishment of the actions specified in
the service bulletin is intended to adequately address the identified
unsafe condition.
Related ADs
This AD provides an optional terminating action for the repetitive
inspections by accomplishment of the modification of the nacelle strut
and wing structure required by the following ADs:
AD 2000-19-09, amendment 39-11910 (65 FR 58641, October 17, 2000),
which is applicable to certain Boeing Model 767 series airplanes
powered by Rolls-Royce RB211 series engines;
AD 2001-02-07, amendment 39-12091 (66 FR 8085, March 5, 2001),
which is applicable to certain Boeing Model 767 series airplanes
powered by Pratt & Whitney engines; and
AD 2001-06-12, amendment 39-12159 (66 FR 17492, May 7, 2001), which
is applicable to certain Boeing Model 767 series airplanes powered by
General Electric engines.
All the previous ADs require prior or concurrent accomplishment of
the following service bulletins, which are specified in Service
Bulletin 767-54A0062, Revision 5, as the appropriate sources of service
information for accomplishment of the rework of the side load fitting
and tension fasteners, as applicable, and replacement of midspar fuse
pins or modification of the nacelle strut and wing structure. Doing
either of these actions would eliminate the need for the repetitive
inspections specified in Service Bulletin 767-54A0062, Revision 5.
[sbull] Boeing Service Bulletin 767-54-0069, Revision 1, dated
January 29, 1998, describes procedures for rework of the side load
fitting and tension fasteners, as applicable, and replacement of
midspar fuse pins with new, higher-strength midspar fuse pins. The
rework involves increasing the size of the tension bolts of the inboard
and outboard side load fittings. The replacement also involves
installing new, higher-strength bolts and radius fillers in the side
load fittings and backup support structure, and installing higher-
strength fasteners common to the front spar and rib number 8 rib post.
[sbull] Boeing Service Bulletin 767-54-0080, dated October 7, 1999,
describes procedures for modification of the nacelle strut and wing
structure. The modification consists of replacing many of the
significant load-bearing components of the strut (e.g., the side link
fittings assemblies, the midspar fittings, the side load fittings,
certain fuse bolt assemblies) with improved components.
[sbull] Boeing Service Bulletin 767-54-0081, dated July 29, 1999,
describes procedures for modification of the nacelle strut and wing
structure. The modification consists of replacing many of the
significant load-bearing components of the strut and wing (e.g., the
side link fittings, the midspar fittings, the side load fittings,
certain fuse pin assemblies) with improved components.
[sbull] Boeing Service Bulletin 767-54-0082, dated October 28,
1999, describes procedures for modification of the nacelle strut and
wing structure. The modification consists of replacing many of the
significant load-bearing components of the strut-to-wing attachment
(e.g., midspar fuse pins, side links, side link fuse pins, diagonal
brace, and diagonal brace fuse pins) with improved components.
Explanation of Requirements of Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of this same type design, this AD
supersedes AD 94-11-02 to continue to require repetitive detailed and
eddy current inspections to detect cracks of certain midspar fuse pins,
and replacement of any cracked midspar fuse pin with a new fuse pin.
This AD reduces certain compliance times for certain inspections,
expands certain detailed and eddy current inspections, and limits the
applicability in the existing AD.
Difference Between This AD and Service Bulletin
Boeing Alert Service Bulletin 767-54A0062, Revision 5, specifies
that all actions for which the Boeing 767 Airplane Maintenance Manual
(AMM) is specified as the appropriate source of service information for
work instructions may instead be done according to an ``operator's
equivalent procedure.'' However, this AD requires that engine removal
and support, when any fuse pin is removed from a strut, must be
accomplished per the procedures specified the applicable section of the
AMM. An ``operator's equivalent procedure'' may be used only if
approved as an alternative method of compliance per paragraph (o)(1) of
this AD.
Explanation of Change Made to Existing Requirements
The FAA has changed all references to a ``detailed visual
inspection'' in the existing AD to ``detailed inspection'' in this AD.
Additionally, a note has been
[[Page 4376]]
added to this AD to define that inspection.
Determination of Rule's Effective Date
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications shall identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Submit comments using the following format:
[sbull] Organize comments issue-by-issue. For example, discuss a
request to change the compliance time and a request to change the
service bulletin reference as two separate issues.
[sbull] For each issue, state what specific change to the AD is
being requested.
[sbull] Include justification (e.g., reasons or data) for each
request.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2002-NM-308-AD.'' The postcard will be date stamped
and returned to the commenter.
Regulatory Impact
The regulations adopted herein 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. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, may be obtained from the Rules Docket at the
location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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. Section 39.13 is amended by removing amendment 39-8918 (59 FR
27229, June 10, 1994), and by adding a new airworthiness directive
(AD), amendment 39-13026, to read as follows:
2003-03-02 Boeing: Amendment 39-13026. Docket 2002-NM-308-AD.
Supersedes AD 94-11-02, Amendment 39-8918.
Applicability: Model 767-200, -300, and -300F series airplanes,
as listed in Boeing Alert Service Bulletin 767-54A0062, Revision 5,
dated November 11, 2002; certificated in any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
modified, altered, or repaired in the area subject to the
requirements of this AD. For airplanes that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (o)(1)
of this AD. The request should include an assessment of the effect
of the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent loss of the strut and engine due to corrosion damage
and cracking of both fuse pins on the same strut, accomplish the
following:
Restatement of Requirements of AD 94-11-02
Repetitive Inspections
(a) For airplanes having midspar fuse pins, part number (P/N)
311T3102-1: Perform a detailed inspection and an eddy current
inspection to detect cracks of the midspar fuse pins, in accordance
with Boeing Alert Service Bulletin 767-54A0062, dated April 14,
1994; or Boeing Alert Service Bulletin 767-54A0062, Revision 5,
dated November 11, 2002; at the time specified in paragraph (a)(1),
(a)(2), (a)(3), or (a)(4) of this AD, as applicable. Repeat these
inspections thereafter at intervals not to exceed 3,000 landings
until accomplishment of the initial inspections specified in
paragraph (h) of this AD.
Note 2: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
(1) For airplanes having midspar fuse pins that have accumulated
18,000 or more total landings as of June 10, 1994 (the effective
date of AD 94-11-02, amendment 39-8918), accomplish the inspections
within 60 days after June 10, 1994.
(2) For airplanes having midspar fuse pins that have accumulated
15,000 or more total landings, but less than 18,000 total landings,
as of June 10, 1994, accomplish the inspections within 90 days after
June 10, 1994.
[[Page 4377]]
(3) For airplanes having midspar fuse pins that have accumulated
10,000 or more total landings, but less than 15,000 total landings,
as of June 10, 1994, accomplish the inspections within 120 days
after June 10, 1994.
(4) For airplanes having midspar fuse pins that have accumulated
less than 10,000 total landings as of June 10, 1994, accomplish the
inspections prior to the accumulation of 10,000 total landings on
the fuse pin, or within 120 days after June 10, 1994, whichever
occurs later.
(b) For airplanes having a midspar fuse pin, P/N 311T3102-2 or
311T2102-1: Prior to the accumulation of 15,000 total landings on
the fuse pin, or within 90 days after June 10, 1994, whichever
occurs later, perform a detailed inspection and an eddy current
inspection to detect cracks on the midspar fuse pins, in accordance
with Boeing Alert Service Bulletin 767-54A0062, dated April 14,
1994; or Boeing Alert Service Bulletin 767-54A0062, Revision 5,
dated November 11, 2002. Repeat these inspections thereafter at
intervals not to exceed 3,000 landings until accomplishment of
paragraph (h) of this AD.
Replacement/Repetitive Inspections
(c) If any crack is found during an inspection required by
paragraph (a) or (b) of this AD, prior to further flight, replace
the cracked midspar fuse pin with a new fuse pin, in accordance with
Boeing Alert Service Bulletin 767-54A0062, dated April 14, 1994; or
Boeing Alert Service Bulletin 767-54A0062, Revision 5, dated
November 11, 2002. Thereafter, perform the detailed and eddy current
inspections specified in paragraph (a) or (b) of this AD, as
applicable, on the new fuse pin at the time specified in paragraph
(c)(1) or (c)(2) of this AD.
(1) For airplanes having midspar fuse pins, P/N 311T3102-1:
Perform the initial inspection of the new fuse pin prior to the
accumulation of 10,000 total landings on the new fuse pin. Repeat
the inspection thereafter at intervals not to exceed 3,000 landings
until accomplishment of paragraph (j) of this AD.
(2) For airplanes having midspar fuse pins, P/Ns 311T3102-2 and
311T2102-1: Perform the initial inspection of the new fuse pin prior
to the accumulation of 15,000 total landings on the new fuse pin.
Repeat the inspection thereafter at intervals not to exceed 3,000
landings until accomplishment of paragraph (j) of this AD.
Fuse Pin Removal
(d) When any fuse pin is removed from a strut equipped with a
General Electric engine, the engine must be removed in accordance
with procedures described in the Boeing 767 Maintenance Manual,
subject 71-00-02; or supported in accordance with a method approved
by the Manager, Seattle Aircraft Certification Office (ACO), FAA,
Transport Airplane Directorate.
(e) When any fuse pin is removed from a strut equipped with a
Pratt & Whitney engine, the engine must be removed in accordance
with procedures described in the Boeing 767 Maintenance Manual,
subject 71-00-02; or supported in accordance with procedures
described in the Boeing 767 Maintenance Manual, subject 54-51-02,
Temporary Revisions (TR), dated April 22, 1994; or supported in
accordance with a method approved by the Manager, Seattle ACO.
(f) When any fuse pin is removed from a strut equipped with a
Rolls-Royce engine, the engine must be removed in accordance with
procedures described in the Boeing 767 Maintenance Manual, subject
71-00-02; or supported in accordance with procedures described in
the Boeing 767 Maintenance Manual, subject 54-51-02; or supported in
accordance with a method approved by the Manager, Seattle ACO.
(g) Any midspar fuse pin, P/N 311T3102-1, 311T3102-2, or
311T2102-1, that has been removed from the strut and inspected for
cracks using the 100 percent magnetic particle inspection technique
described in Boeing Alert Service Bulletin 767-54A0062, dated April
14, 1994; or Boeing Alert Service Bulletin 767-54A0062, Revision 5,
dated November 11, 2002; may be reinstalled on the strut provided
that the fuse pin is found to be crack-free during the magnetic
particle inspection. Prior to the accumulation of 3,000 total
landings after reinstallation of the fuse pin, the fuse pin must be
inspected in accordance with the requirements of paragraph (a), (b),
or (h) of this AD, as applicable.
New Requirements of this AD
Initial and Repetitive Inspections
(h) For airplanes having midspar fuse pins, P/Ns 311T3102-1,
311T3102-2, 311T3102-3, 311T3102-4, 311T2102-1 or 311T2102-2: Do a
detailed inspection and an eddy current inspection for cracks and
corrosion per Boeing Alert Service Bulletin 767-54A0062, Revision 5,
dated November 11, 2002. Do the inspections at the later of the
times specified in paragraphs (h)(1) and (h)(2) of this AD. Repeat
the inspections at least every 3,000 landings or 5 years, whichever
is first. Accomplishment of the initial inspections in this
paragraph ends the repetitive inspections required by paragraphs (a)
and (b) of this AD.
(1) Before the accumulation of 5,000 total landings on the fuse
pin or within 5 years after fuse pin installation, whichever is
first.
(2) Within 30 days after the effective date of this AD.
Corrective Action
(i) If any crack or corrosion is found during any inspection
required by paragraph (h) of this AD, before further flight, do the
actions required by paragraph (i)(1) or (i)(2) of this AD, as
applicable, per Boeing Alert Service Bulletin 767-54A0062, Revision
5, dated November 11, 2002.
(1) If any crack is found, replace the midspar fuse pin with a
new fuse pin.
(2) If any corrosion is found, repair the midspar fuse pin or
replace with a new fuse pin.
Repetitive Inspections
(j) For airplanes identified in paragraph (h) of this AD: After
the installation of a new midspar fuse pin, inspect the new fuse pin
per paragraph (h) of this AD before the accumulation of 5,000 total
landings on the fuse pin or within 5 years, whichever is first.
Repeat the inspections at least every 3,000 landings or 5 years,
whichever is first Accomplishment of this paragraph ends the
repetitive inspections required by paragraph (c) of this AD.
Optional Terminating Action
(k) For all airplanes: Accomplishment of the rework of the side
load fitting and tension fasteners, as applicable, and replacement
of midspar fuse pins per Boeing Service Bulletin 767-54-0069, dated
October 9, 1997; Revision 1, dated January 29, 1998; or Revision 2,
dated August 31, 2000; ends the repetitive inspections required by
this AD.
(l) Modification of the nacelle strut and wing structure as
required by AD 2000-19-09, amendment 39-11910 (applicable to certain
Boeing Model 767 series airplanes powered by Rolls-Royce RB211
series engines); AD 2001-02-07, amendment 39-12091 (applicable to
certain Boeing Model 767 series airplanes powered by Pratt & Whitney
engines); or AD 2001-06-12, amendment 39-12159 (applicable to
certain Boeing Model 767 series airplanes powered by General
Electric engines); as applicable; ends the repetitive inspections
required by this AD.
[[Page 4378]]
``Operator's Equivalent Procedure''
(m) Though Boeing Alert Service Bulletin 767-54A0062, Revision
5, dated November 11, 2002, specifies that an ``operator's
equivalent procedure'' may be used for all actions for which the
Boeing 767 Airplane Maintenance Manual (AMM) is specified as the
appropriate source of service information: Engine removal and
support, when any fuse pin is removed from a strut, must be done
according to the applicable section of the Boeing 767 Airplane
Maintenance Manual, as specified in the service bulletin.
Actions Done per Previously Issued Service Information
(n) Inspections and replacements done before the effective date
of this AD per Boeing Alert Service Bulletin 767-54A0062, Revision
1, dated May 11, 1994; Revision 2, dated December 21, 1994; Revision
3, dated June 15, 1995; or Revision 4, dated May 7, 1998; are
acceptable for compliance with the applicable actions specified in
this AD.
Alternative Methods of Compliance
(o)(1) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, Seattle ACO. Operators shall submit
their requests through an appropriate FAA Principal Maintenance
Inspector, who may add comments and then send it to the Manager,
Seattle ACO.
(2) Alternative methods of compliance, approved previously in
accordance with AD 94-11-02, amendment 39-8918, are approved as
alternative methods of compliance with the applicable actions
specified in this AD.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Seattle ACO.
Special Flight Permits
(p) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
Incorporation by Reference
(q) Unless otherwise provided in this AD, the actions shall be
done in accordance with Boeing Alert Service Bulletin 767-54A0062,
dated April 14, 1994; and Boeing Alert Service Bulletin 767-54A0062,
Revision 5, dated November 11, 2002.
(1) The incorporation by reference of Boeing Alert Service
Bulletin 767-54A0062, Revision 5, dated November 11, 2002, is
approved by the Director of the Federal Register in accordance with
5 U.S.C. 552(a) and 1 CFR part 51.
(2) The incorporation by reference of Boeing Alert Service
Bulletin 767-54A0062, dated April 14, 1994, was approved previously
by the Director of the Federal Register as of June 10, 1994 (59 FR
27229, May 26, 1994).
(3) Copies may be obtained from Boeing Commercial Airplane
Group, PO Box 3707, Seattle, Washington 98124-2207. Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
Effective Date
(r) This amendment becomes effective on February 13, 2003.
Issued in Renton, Washington, on January 22, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-1827 Filed 1-28-03; 8:45 am]
BILLING CODE 4910-13-P