[Federal Register Volume 59, Number 52 (Thursday, March 17, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-6210]
[[Page Unknown]]
[Federal Register: March 17, 1994]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 93-NM-216-AD]
Airworthiness Directives; McDonnell Douglas Model MD-11 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to certain McDonnell Douglas
Model MD-11 series airplanes, that currently requires inspections to
verify the installation of shear pins, shear pin retainers, and shear
pin retainer attaching parts in the aft end of the center pylon thrust
link, and repair, if necessary. That AD also provides an optional
terminating action, which, if accomplished, would terminate the
repetitive inspections. That AD was prompted by a report that both
shear pins that attach the aft end of the center engine pylon thrust
link to the tail pylon were missing. This action would add inspections
to verify that the shear pin retainer attaching parts are tightened
within specified limits; and a terminating modification for those
inspections. This action would also remove the optional terminating
action, and expand the applicability of the rule to include additional
airplanes. The actions specified by the proposed AD are intended to
prevent structural damage to the engine mount structure, which could
lead to loss of airplane components.
DATES: Comments must be received by May 10, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 93-NM-216-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.
The service information referenced in the proposed rule may be
obtained from McDonnell Douglas Corporation, P.O. Box 1771, Long Beach,
CA 90801-1771, Attention: Business Unit Manager, Technical
Administrative Support, Dept. L51, M.C. 2-98. This information may be
examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue,
SW., Renton, Washington; or at the FAA, Transport Airplane Directorate,
Los Angeles Aircraft Certification Office (ACO), 3229 East Spring
Street, Long Beach, California.
FOR FURTHER INFORMATION CONTACT: Wahib Mina, Aerospace Engineer,
Airframe Branch, ANM-121L, FAA, Transport Airplane Directorate, Los
Angeles Aircraft Certification Office (ACO), 3229 East Spring Street,
Long Beach, California 90806-2425; telephone (310) 988-5324; fax (310)
988-5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 93-NM-216-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules
Docket No. 93-NM-216-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On October 14, 1992, the FAA issued AD 92-23-03, Amendment 39-8403
(57 FR 47991, October 21, 1992), applicable to certain McDonnell
Douglas Model MD-11 series airplanes, to require repetitive visual
inspections to verify the installation of shear pins, shear pin
retainers, and shear pin retainer attaching parts at the aft end of the
center engine (No. 2) pylon thrust link; repair of any discrepancy
found; and submission of a report of inspection findings to the FAA.
That AD also provides an optional terminating action for the repetitive
inspections. That AD was prompted by a report that both shear pins that
attach the aft end of the center engine pylon thrust link to the tail
pylon were missing. The requirements of that AD are intended to prevent
structural damage to the engine mount structure, which could lead to
loss of airplane components.
Since the issuance of AD 92-23-03, one operator has reported that,
during the initial visual inspection conducted in accordance with that
AD, all bolts and nuts were found installed; however, during a
subsequent repetitive inspection, one nut and one bolt that attach the
retainer were missing. If the retainers are missing, the shear pins may
also be missing and the engine thrust loads will be improperly
distributed to the airplane structure. This condition, if not
corrected, could result in structural damage to the engine mount
structure, which could lead to loss of airplane components.
The FAA has reviewed and approved McDonnell Douglas MD-11 Alert
Service Bulletin A54-31, Revision 1, dated June 3, 1993. This service
bulletin revision adds procedures for performing repetitive inspections
to verify that the shear pin retainer attaching parts are tightened
within specific limits. This service bulletin revision also describes
procedures for replacement of the existing retainer and attaching parts
with a new retainer and attaching parts. Incorporation of this
replacement eliminates the need for repetitive visual inspections and
repetitive tightness verifications. The effectivity listing of this
service bulletin revision includes 34 additional airplanes identified
as being subject to the addressed unsafe condition.
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would supersede AD 92-23-03 to continue to require
repetitive visual inspections to verify the installation of the shear
pins, the shear pin retainers, and the shear pin retainer attaching
parts in the aft end of the center engine (No. 2) pylon thrust link.
The proposed AD would add repetitive inspections to verify that the
shear pin retainer attaching parts are tightened within specified
limits. If any shear pin, shear pin retainer, or shear pin retainer
attaching part is missing during any inspection, this proposal would
continue to require repair in accordance with a method approved by the
FAA. The ``optional terminating action'' provided by AD 92-23-03, which
consists of a one-time verification for tightness of the nuts of the
four shear pin retainer attaching bolts, would no longer be provided in
the proposed rule.
The proposed AD would also require eventual replacement of the
existing retainer and attaching parts with a new retainer and attaching
parts. When accomplished, this replacement would be considered
terminating action for the currently required repetitive visual
inspections and the proposed repetitive verifications of tightness. The
actions would be required to be accomplished in accordance with the
revised alert service bulletin described previously.
This proposal would also require that operators submit a report to
the FAA of any discrepancy found during any inspection.
Additionally, this proposal would expand the applicability of the
rule to include additional airplanes that have been identified as being
subject to the addressed unsafe condition.
There are approximately 94 Model MD-11 series airplanes of the
affected design in the worldwide fleet. The FAA estimates that 42
airplanes of U.S. registry would be affected by this proposed AD, that
it would take approximately 16 work hours per airplane to accomplish
the proposed actions and that the average labor rate is $55 per work
hour. Required parts would be provided at no cost to operators. Based
on these figures, the total cost impact of the proposed AD on U.S.
operators is estimated to be $36,960, or $880 per airplane.
The total cost impact figure discussed above is based on
assumptions that no operator has yet accomplished any of the proposed
requirements of this AD action, and that no operator would accomplish
those actions in the future if this AD were not adopted.
The regulations proposed herein would not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that 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) if promulgated, 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. A copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 14
CFR part 39 of the Federal Aviation Regulations as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-8403 (57 FR
47991, October 21, 1992), and by adding a new airworthiness directive
(AD), to read as follows:
McDonnell Douglas: Docket 93-NM-216-AD. Supersedes AD 92-23-03,
Amendment 39-8403.
Applicability: Model MD-11 series airplanes; as listed in
McDonnell Douglas MD-11 Alert Service Bulletin A54-31, dated
September 17, 1992, and McDonnell Douglas MD-11 Alert Service
Bulletin A54-31, Revision 1, dated June 3, 1993; certificated in any
category.
Compliance: Required as indicated, unless accomplished
previously. -
To prevent structural damage to the engine mount structure,
which could lead to loss of airplane components, accomplish the
following:
(a) For airplanes listed in McDonnell Douglas MD-11 Alert
Service Bulletin A54-31, dated September 17, 1992: Within 15 days
after November 5, 1992 (the effective date of AD 92-23-03, Amendment
39-8403), unless previously accomplished within the last 30 days,
perform a visual inspection of the thrust link of the center engine
forward mount to verify installation of the shear pins, the shear
pin retainers, and the shear pin retainer attaching parts in
accordance with McDonnell Douglas MD-11 Alert Service Bulletin A54-
31, dated September 17, 1992, or Revision 1, dated June 3, 1993.
(1) If shear pins, shear pin retainers, and shear pin retainer
attaching parts are installed, repeat the inspection required by
paragraph (a) of this AD thereafter at intervals not to exceed 60
days in accordance with the service bulletin until accomplishment of
paragraph (d) of this AD.
(2) If any shear pin, shear pin retainer, or shear pin retainer
attaching part is missing, prior to further flight, repair in
accordance with a method approved by the Manager, Los Angeles
Aircraft Certification Office (ACO), FAA, Transport Airplane
Directorate. Repeat the inspection required by paragraph (a) of this
AD thereafter at intervals not to exceed 60 days in accordance with
the service bulletin until accomplishment of paragraph (d) of this
AD.
(b) For airplanes listed in McDonnell Douglas MD-11 Alert
Service Bulletin A54-31, Revision 1, dated June 3, 1993, and not
subject to the requirements of paragraph (a) of this AD: Within 15
days after the effective date of this AD, unless previously
accomplished within the last 30 days, perform a visual inspection of
the thrust link of the center engine forward mount to verify
installation of the shear pins, the shear pin retainers, and the
shear pin retainer attaching parts in accordance with McDonnell
Douglas MD-11 Alert Service Bulletin A54-31, Revision 1, dated June
3, 1993.
(1) If shear pins, shear pin retainers, and shear pin retainer
attaching parts are installed, repeat the inspection required by
paragraph (b) of this AD thereafter at intervals not to exceed 60
days in accordance with the service bulletin until accomplishment of
paragraph (d) of this AD.
(2) If any shear pin, shear pin retainer, or shear pin retainer
attaching part is missing, prior to further flight, repair in
accordance with a method approved by the Manager, Los Angeles
Aircraft Certification Office (ACO), FAA, Transport Airplane
Directorate. Repeat the inspection required by paragraph (b) of this
AD thereafter at intervals not to exceed 60 days in accordance with
the service bulletin until accomplishment of paragraph (d) of this
AD.
(c) Within 18 months after the effective date of this AD, verify
that the tightness of the shear pin retainer attaching parts is
within the limits specified in accordance with McDonnell Douglas MD-
11 Alert Service Bulletin A54-31, Revision 1, dated June 3, 1993.
Repeat the verification required by paragraphs (c) of this AD
thereafter at intervals not to exceed 18 months in accordance with
the service bulletin until accomplishment of paragraph (d) of this
AD.
(d) Within 3 years after the effective date of this AD, replace
the existing retainer and bolts with safety wire with a new retainer
and new bolts with safety wire in accordance with McDonnell Douglas
MD-11 Alert Service Bulletin A54-31, Revision 1, dated June 3, 1993.
Accomplishment of this replacement constitutes terminating action
for the repetitive actions required by paragraphs (a), (b) and (c)
of this AD.
(e) Within 15 days after detecting any discrepancy during any
inspection or verification action required by this AD, submit a
report of the inspection results to the Manager, Los Angeles ACO,
FAA, Transport Airplane Directorate, 3229 East Spring Street, Long
Beach, California 90806-2425; fax (310) 988-5210. Information
collection requirements contained in this regulation have been
approved by the Office of Management and Budget (OMB) under the
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et
seq.) and have been assigned OMB Control Number 2120-0056.
(f) 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, Los Angeles ACO, FAA, Transport
Airplane Directorate. Operators shall submit their requests through
an appropriate FAA Principal Maintenance Inspector, who may add
comments and then send it to the Manager, Los Angeles ACO.
Note: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles ACO. -
(g) Special flight permits may be issued in accordance with
Federal Aviation Regulations (FAR) 21.197 and 21.199 to operate the
airplane to a location where the requirements of this AD can be
accomplished.
Issued in Renton, Washington, on March 11, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-6209 Filed 3-16-94; 8:45 am]
BILLING CODE 4910-13-U
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-05-AD]
Airworthiness Directives; Boeing Model 747 Series Airplanes
Equipped With Pratt & Whitney JT9D-3 or JT9D-7 Series Engines,
Excluding JT9D-70 Series Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Boeing Model 747 series
airplanes. This proposal would require inspections of the inboard and
outboard strut chords, stiffeners, and web to detect cracks and loose
fasteners; repair of the chords, stiffeners, or web, if necessary; and
replacement of any loose fastener. This proposal is prompted by reports
of fatigue cracks and loose fasteners found in the forward lower spar
web of the inboard strut on Model 747 series airplanes equipped with
Pratt & Whitney JT9D-3 and JT9D-7 series engines. The actions specified
by the proposed AD are intended to prevent separation of the strut from
the wing of the airplane due to fatigue cracking.
DATES: Comments must be received by May 10, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-05-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.
The service information referenced in the proposed rule may be
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle,
Washington 98124-2207. This information may be examined at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056; telephone (206) 227-2776; fax (206) 227-1181.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 94-NM-05-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules
Docket No. 94-NM-05-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received six reports of fatigue cracks and one report
of loose fasteners found in the forward lower spar web of the inboard
strut on Model 747 series airplanes equipped with Pratt & Whitney JT9D-
3 and JT9D-7 series engines. The cracks were found in the area under
the stiffeners and baffle and along the web chord. The airplanes on
which these cracks were found had accumulated between 6,451 and 18,350
flight cycles and between 17,797 and 83,960 flight hours. All cracks
reported have been found on the web of the inboard strut.
During investigation of a recent in-flight engine loss, a similar
crack of approximately two inches in length was found on the forward
lower spar web. Although the in-inflight engine loss incident is still
under investigation, the crack in the web was determined to be a
contributing cause of the accident.
Cracking in the forward lower spar web of the inboard strut could
reduce the lateral strength of the strut. This condition, if not
detected and corrected in a timely manner, could result in separation
of the strut from the wing of the airplane due to fatigue cracking.
Although all cracks reported were found on the web of the inboard
strut, given standard design tolerances, little difference exists
between the thickness of the web of the inboard strut (0.025 inch) and
that of the outboard strut (0.032 inch). Additionally, the inboard and
outboard webs are similar in configuration and loading environments.
For these reasons, the FAA finds that the outboard strut web is subject
to the same unsafe condition as the inboard strut web.
The FAA has reviewed and approved Boeing Service Bulletin 747-54-
2160, dated September 9, 1993, that describes procedures for repetitive
detailed visual inspections of the inboard strut chords, stiffeners,
and web to detect cracks and loose fasteners; repair of the chords,
stiffeners, or web, if necessary; and replacement of any loose fastener
found. These same procedures are effective for inspecting the outboard
strut chord.
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would require repetitive detailed visual inspections of the
inboard and outboard strut chords, stiffeners, and web to detect cracks
and loose fasteners; repair of the chords, stiffeners, or web, if
necessary; and replacement of any loose fastener. The actions would be
required to be accomplished in accordance with the procedures specified
in the service bulletin described previously.
This is considered to be interim action. The manufacturer has
advised that it is currently developing a modification program for the
engine strut that will positively address the unsafe condition
addressed by this AD. Once this modification program is developed,
approved, and available, the FAA may consider additional rulemaking.
There are approximately 380 Model 747 series airplanes of the
affected design in the worldwide fleet. The FAA estimates that 140
airplanes of U.S. registry would be affected by this proposed AD, that
it would take approximately 22 work hours per airplane to accomplish
the proposed actions, and that the average labor rate is $55 per work
hour. Based on these figures, the total cost impact of the proposed AD
on U.S. operators is estimated to be $169,400, or $1,210 per airplane.
The total cost impact figure discussed above is based on
assumptions that no operator has yet accomplished any of the proposed
requirements of this AD action, and that no operator would accomplish
those actions in the future if this AD were not adopted.
The regulations proposed herein would not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that 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) if promulgated, 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. A copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 14
CFR part 39 of the Federal Aviation Regulations as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
Boeing: Docket 94-NM-05-AD.
Applicability: Model 747 series airplanes equipped with Pratt &
Whitney JT9D-3 or JT9D-7 series engines, excluding JT9D-70 series
engines; line numbers 001 through 510 inclusive; certificated in any
category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent separation of the strut from the wing of the airplane
due to fatigue cracking, accomplish the following:
(a) Perform a detailed visual inspection of the inboard and
outboard strut forward lower spar chords, stiffeners, and web to
detect cracks and loose fasteners, in accordance with the procedures
described in Boeing Service Bulletin 747-54-2160, dated September 9,
1993, at the time specified in paragraph (a)(1), (a)(2), or (a)(3)
of this AD, as applicable. Repeat this inspection thereafter at
intervals not to exceed 2,000 landings or 8,000 hours time-in-
service, whichever occurs first.
(1) For airplanes that have accumulated less than 6,000 total
landings as of the effective date of this AD: Perform the initial
inspection at the later of the times specified in paragraphs
(a)(1)(i) and (a)(1)(ii) of this AD.
(i) Prior to the accumulation of 6,000 total landings on the
strut. Or
(ii) Within 8 months after the effective date of this AD.
(2) For airplanes that have accumulated 6,000 or more total
landings, but less than 15,000 total landings, as of the effective
date of this AD: Perform the initial inspection within 6 months
after the effective date of this AD.
(3) For airplanes that have accumulated 15,000 or more total
landings as of the effective date of this AD: Perform the initial
inspection within 4 months after the effective date of this AD.
(b) If any crack is found during any inspection required by
paragraph (a) of this AD, prior to further flight, repair in
accordance with procedures specified in Chapter 54-10-03 of the 747
Structural Repair Manual.
(c) If any loose fastener is found during any inspection
required by paragraph (a) of this AD, prior to further flight,
replace the fastener in accordance with procedures specified in
Chapter 51-30-02 of the 747 Structural Repair Manual.
(d) 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 Aircraft Certification
Office (ACO), FAA, Transport Airplane Directorate. 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.
Note: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Seattle ACO.
(e) Special flight permits may be issued in accordance with
Federal Aviation Regulations (FAR) 21.197 and 21.199 to operate the
airplane to a location where the requirements of this AD can be
accomplished.
Issued in Renton, Washington, on March 11, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-6210 Filed 3-16-94; 8:45 am]
BILLING CODE 4910-13-U
