[Federal Register Volume 62, Number 14 (Wednesday, January 22, 1997)]
[Rules and Regulations]
[Pages 3200-3204]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-815]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-CE-46-AD; Amendment 39-9884; AD 97-01-13]
Airworthiness Directives; Cessna Aircraft Company 100, 200, 300,
and 400 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to Cessna Aircraft Company (Cessna) 100, 200, 300, and 400
series airplanes. This action requires checking the airplane
maintenance records for any fuel, oil, or hydraulic hose, Cessna part
number (P/N) S51-10, replaced between March 1995 and February 3, 1997
(the effective date of this AD); immediately checking any of these
hoses for a diagonal or spiral external reinforcement wrap; and
immediately replacing any of these hoses that have a diagonal or spiral
external reinforcement wrap with one that has a criss-cross external
reinforcement wrap. This action was prompted by reports of operators
experiencing a loss of engine power because of low fuel feed, in
addition to Cessna discovering that the rubber hose installed at the
factory on certain Cessna Models 208 and 208B airplanes was defective.
The Cessna P/N S51-10 rubber hose is utilized on fuel, oil, and
hydraulic hoses on the affected airplanes. The actions specified by
this AD are intended to prevent fuel, oil, or hydraulic systems failure
caused by a collapsed hose.
DATES: Effective February 3, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 3, 1997.
Comments for inclusion in the Rules Docket must be received on or
before March 17, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket 96-CE-46-AD, Room 1558, 601 E. 12th
Street, Kansas City, Missouri 64106.
Service information that applies to this AD may be obtained from
Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita,
Kansas 67277, telephone (316) 941-7550; facsimile (316) 942-9006. This
information may also be examined at the Federal Aviation Administration
(FAA), Central Region, Office of the Assistant Chief Counsel,
Attention: Rules Docket 96-CE-46-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106; or at the Office of the Federal Register,
800 North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: John C. Pearson, Aerospace Engineer,
FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room
100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946-
4134, facsimile (316) 946-4407.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA has recently received several incident reports of fuel flow
blockage to the engines of certain Cessna 208 series airplanes.
Examination of the Cessna part number (P/N) S51-10 rubber hoses
installed on these airplanes revealed a deterioration to the point of
delamination of the inner tube from the external wrap. This rubber hose
is utilized on fuel, oil, and hydraulic hoses on Cessna 100, 200, 300,
and 400 series airplanes. This kind of deterioration eventually causes
the rubber hose to collapse, which could result in failure of the fuel,
oil, or hydraulic systems.
Further investigation revealed this particular rubber hose was
manufactured by Buckeye Rubber Products Company in January 1995, and
Cessna purchased 300 feet of this hose for factory installation on
certain Cessna Models 208 and 208B airplanes between March 1995 and
June 1995. The
[[Page 3201]]
remaining portion of hose was distributed in March 1995 as replacement
hose. With this in mind, the Cessna P/N S51-10 hose could be installed
by field approval on any Cessna 100, 200, 300, and 400 series
airplanes, as well as at manufacture on certain Cessna Models 208 and
208B airplanes.
Relative Service Information
Cessna has issued the service bulletins presented below, which
include ACCOMPLISHMENT INSTRUCTIONS for (1) Checking for the
installation of fuel, oil, and hydraulic hoses, Cessna P/N S51-10, with
a diagonal or spiral external reinforcement wrap, and (2) replacing any
of these hoses that have a diagonal or spiral external reinforcement
wrap with one that has a criss-cross external reinforcement wrap:
--REIMS/CESSNA Service Bulletin (SB) CAB96-21, dated October 18,
1996; Model Affected: F406
--Cessna Aircraft Company SB CQB96-3, dated October 18, 1996; Model
Affected: 425
--Cessna Aircraft Company SB SEB96-15, dated October 18, 1996;
Models Affected: 150, 150A, 150B, 150C, 150D, 150E, 150F, 150G,
150H, 150J, 150K, 150L, 150M, A150K, A150L, A150M, F150F, F150G,
F150H, F150J, F150K, F150L, F150M, FA150K, FA150L, FRA150L, FRA150M,
152, A152, F152, FA152, 172, 172A, 172B, 172C, 172D, 172E, 172F,
172G, 172H, 172I, 172K, 172L, 172M, 172N, 172P, 172Q, FP172, F172D,
F172E, F172F, F172G, F172H, F172K, F172L, F172M, F172N, F172P,
FR172E, FR172F, FR172G, FR172H, FR172J, FR172K, 175, 175A, 175B,
175C, P172D, R172E(T41), R172F(T41), R172G(T41), R172H(T41), R172J,
R172K, 172RG, 177, 177A, 177B, 177RG, F177RG, 180, 180A, 180B, 180C,
180D, 180E, 180F, 180G, 180H, 180J, 180K, 182,182A, 182B, 182C,
182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P,
182Q, 182R, F182P, F182Q, FR182, R182, T182, TR182, 185, 185A, 185B,
185C, 185D, 185E, A185E, A185F, 188, 188A, 188B, A188, A188A, A188B,
T188C, 206, U206, U206A, U206B, U206C, U206D, U206E, U206F, U206G,
TU206A, TU206B, TU206C, TU206D, TU206E, TU206F, TU206G, P206A,
P206B, P206C, P206D, P206E, TP206, TP206A, TP206B, TP206C, TP206D,
TP206E, 207, 207A, T207, T207A, 210, 210-5 (205), 210-5A, (205A),
210A, 210B, 210C, 210D, 210E, 210F, 210G, 210H, 210J, 210K, 210L,
210M, 210N, 210R, P210N, P210R, and T210F.
--Cessna Aircraft Company SB CAB96-15, Revision 1, October 18, 1996;
Models Affected: 208 and 208B.
--Cessna Aircraft Company SB MEB96-10, dated October 18, 1996;
Models Affected: T303, 310P, 310Q, 310R, T310P, 310Q, 310R, 335,
336, 337, 337A, 337B, 337C, 337D, 337E, 337F, 337G, 337H, F337E,
F337F, F337G, F337H, FT337E, FT337F, FT337GP, FT337HP, FTB337 T337B,
T337C, T337D, T337E, T337F, T337G, T337H, T337H-SP, M337B, P337H,
340, 340A, 401, 401A, 401B, 402, 402A, 402B, 402C, 404, 411, 411A,
414, 414A, 421, 421A, 421B, and 421C.
The FAA's Determination
After examining the circumstances and reviewing all available
information related to the incidents described above, including the
referenced service information, the FAA has determined that AD action
should be taken to prevent fuel, oil, or hydraulic systems failure
caused by a collapsed hose.
Explanation of the Provisions of This AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Cessna 100, 200, 300, and 400 series
airplanes of the same type design, the FAA is issuing an AD. This AD
requires checking the airplane maintenance records for any fuel, oil,
or hydraulic hose, Cessna part number (P/N) S51-10, replaced between
March 1995 and February 3, 1997 (the effective date of this AD);
immediately checking any of these hoses for a diagonal or spiral
external reinforcement wrap; and immediately replacing any of these
hoses that have a diagonal or spiral external reinforcement wrap with
one that has a criss-cross external reinforcement wrap. Accomplishment
of the hose check and replacement is required in accordance with the
service bulletins referenced previously.
Determination of the Effective Date of the AD
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for public
prior comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Compliance Time of This AD
The compliance time of this AD is presented in calendar time and
hours time-in-service (TIS). Delamination of the rubber hose inner
tubing and separation of the inner tube from the external wrap is
caused by an error in manufacturing. This condition can develop
regardless of whether the airplane is in flight. The breakdown of the
hose may not be noticed initially, but as the hose continues to erode,
collapse is inevitable, which could result in fuel, oil, or hydraulic
systems failure. For these reasons, the FAA is requiring a compliance
time of specific hours TIS and calendar time (the prevalent one being
that which occurs first).
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting immediate flight safety and, thus, was not
preceded by notice and opportunity to 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 should 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 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.
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 notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 96-CE-46-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
The regulations adopted herein will 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and 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
[[Page 3202]]
(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 (otherwise, an evaluation is
not required). A copy of it, if filed, may be obtained from the Rules
Docket.
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 adding a new airworthiness directive
(AD) to read as follows:
97-01-13 Cessna Aircraft Company: Amendment 39-9884; Docket No. 96-
CE-46-AD.
Applicability: All serial numbers of Models 150, 150A, 150B,
150C, 150D, 150E, 150F, 150G, 150H, 150J, 150K, 150L, 150M, A150K,
A150L, A150M, F150F, F150G, F150H, F150J, F150K, F150L, F150M,
FA150K, FA150L, FRA150L, FRA150M, 152, A152, F152, FA152, 172, 172A,
172B, 172C, 172D, 172E, 172F, 172G, 172H, 172I, 172K, 172L, 172M,
172N, 172P, 172Q, 172RG, FP172, F172D, F172E, F172F, F172G, F172H,
F172K, F172L, F172M, F172N, F172P, FR172E, FR172F, FR172G, FR172H,
FR172J, FR172K, P172D, R172E(T41), R172F(T41), R172G(T41),
R172H(T41), R172J, R172K, 175, 175A, 175B, 175C, 177, 177A, 177B,
177RG, F177RG, 180, 180A, 180B, 180C, 180D, 180E, 180F, 180G, 180H,
180J, 180K, 182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H,
182J, 182K, 182L, 182M, 182N, 182P, 182Q, 182R, F182P, F182Q, FR182,
T182, R182, TR182, 185, 185A, 185B, 185C, 185D, 185E, A185E, A185F,
188, 188A, 188B, A188, A188A, A188B, T188C, 206, P206A, P206B,
P206C, P206D, P206E, TU206A, TU206B, TU206C, TU206D, TU206E, TU206F,
TU206G, TP206, TP206A, TP206B, TP206C, TP206D, TP206E, U206, U206A,
U206B, U206C, U206D, U206E, U206F, U206G, 207, 207A, T207, T207A,
208, 208B, 210, 210A, 210B, 210C, 210D, 210E, 210F, 210G, 210H,
210J, 210K, 210L, 210M, 210N, 210R, T210F, P210N, P210R, 210-5
(205), 210-5A (205A), T303, 310P, 310Q, 310R, T310P, 310Q, 310R,
335, 336, 337, 337A, 337B, 337C, 337D, 337E, 337F, 337G, 337H,
F337E, F337F, F337G, F337H, FT337E, FT337F, FT337GP FT337HP, FTB337,
T337B, T337C, T337D, T337E, T337F, T337G, T337H, T337H-SP, M337B,
P337H, 340, 340A, 401, 401A, 401B, 402, 402A, 402B, 402C, 404, F406,
411, 411A, 414, 414A, 421, 421A, 421B, 421C, and 425 airplanes,
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 (g) 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 in the body of this AD, unless
already accomplished.
To prevent fuel, oil, or hydraulic systems failure caused by a
collapsed hose, accomplish the following:
(a) Within the next 60 hours time-in-service or within the next
60 calendar days, whichever occurs first, check the airplane
maintenance records for any fuel, oil, or hydraulic hose, Cessna
part number (P/N) S51-10, replaced between March 1995 and February
3, 1997 (the effective date of this AD).
(b) Prior to further flight after the check required by
paragraph (a) of this AD, physically check any fuel, oil, or
hydraulic hose, Cessna P/N S51-10, that has been replaced between
March 1995 and February 3, 1997 (the effective date of this AD) for
a diagonal or spiral external reinforcement wrap in accordance with
the ACCOMPLISHMENT INSTRUCTIONS of the applicable service bulletin
presented below:
(1) REIMS/CESSNA Service Bulletin (SB) CAB96-21, dated October
18, 1996; Model Affected: F406
(2) Cessna Aircraft Company SB CQB96-3, dated October 18, 1996;
Model Affected: 425
(3) Cessna Aircraft Company SB SEB96-15, dated October 18, 1996;
Models Affected: 150, 150A, 150B, 150C, 150D, 150E, 150F, 150G,
150H, 150J, 150K, 150L, 150M, A150K, A150L, A150M, F150F, F150G,
F150H, F150J, F150K, F150L, F150M, FA150K, FA150L, FRA150L, FRA150M,
152, A152, F152, FA152, 172, 172A, 172B, 172C, 172D, 172E, 172F,
172G, 172H, 172I, 172K, 172L, 172M, 172N, 172P, 172Q, FP172, F172D,
F172E, F172F, F172G, F172H, F172K, F172L, F172M, F172N, F172P,
FR172E, FR172F, FR172G, FR172H, FR172J, FR172K, 175, 175A, 175B,
175C, P172D, R172E(T41), R172F(T41), R172G(T41), R172H(T41), R172J,
R172K, 172RG, 177, 177A, 177B, 177RG, F177RG, 180, 180A, 180B, 180C,
180D, 180E, 180F, 180G, 180H, 180J, 180K, 182, 182A, 182B, 182C,
182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P,
182Q, 182R, F182P, F182Q, FR182, R182, T182, TR182, 185, 185A, 185B,
185C, 185D, 185E, A185E, A185F, 188, 188A, 188B, A188, A188A, A188B,
T188C, 206, U206, U206A, U206B, U206C, U206D, U206E, U206F, U206G,
TU206A, TU206B, TU206C, TU206D, TU206E, TU206F, TU206G, P206A,
P206B, P206C, P206D, P206E, TP206, TP206A, TP206B, TP206C, TP206D,
TP206E, 207, 207A, T207, T207A, 210, 210-5 (205), 210-5A, (205A),
210A, 210B, 210C, 210D, 210E, 210F, 210G, 210H, 210J, 210K, 210L,
210M, 210N, 210R, P210N, P210R, and T210F.
(4) Cessna Aircraft Company SB CAB96-15, Revision 1, October 18,
1996; Models Affected: 208 and 208B.
(5) Cessna Aircraft Company SB MEB96-10, dated October 18, 1996;
Models Affected: T303, 310P, 310Q, 310R, T310P, 310Q, 310R, 335,
336, 337, 337A, 337B, 337C, 337D, 337E, 337F, 337G, 337H, F337E,
F337F, F337G, F337H, FT337E, FT337F, FT337GP, FT337HP, FTB337 T337B,
T337C, T337D, T337E, T337F, T337G, T337H, T337H-SP, M337B, P337H,
340, 340A, 401, 401A, 401B, 402, 402A, 402B, 402C, 404, 411, 411A,
414, 414A, 421, 421A, 421B, and 421C.
Note 2: Figure 1 of this AD is included to show the diagonal or
spiral external reinforcement wrap on the hose that is referenced in
the check required by paragraph (b) of this AD.
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[GRAPHIC] [TIFF OMITTED] TR22JA97.000
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[[Page 3204]]
(c) Prior to further flight after the check required by
paragraph (b) of this AD, replace any Cessna P/N S51-10 that has a
diagonal or spiral pattern external reinforcement wrap with a Cessna
P/N S51-10 hose that has a criss-cross pattern external wrap.
Accomplish this replacement in accordance with the ACCOMPLISHMENT
INSTRUCTIONS of the applicable service bulletin in paragraph (b) of
this AD.
Note 3: Cessna Model 208 airplanes (serial number 20800241
through 20800258) and Model 208B (serial number 208B0416 through
208B0560) had Cessna P/N S51-10 hoses with a diagonal or spiral
external reinforcement wrap installed at manufacture. All other
airplanes may have had the hose installed by field approval. Cessna
determined that these hoses were available for distribution between
March 28, 1995 and June 28, 1996.
(d) As of the effective date of this AD, no person shall install
a fuel, oil, or hydraulic hose having Cessna P/N S51-10 with a
diagonal or spiral external reinforcement wrap.
(e) The checks required by paragraphs (a) and (b) of this AD may
be performed by the owner/operator holding at least a private pilot
certificate as authorized by section 43.7 of the Federal Aviation
Regulations (14 CFR 43.7), and must be entered into the aircraft
records showing compliance with this AD in accordance with section
43.11 of the Federal Aviation Regulations (14 CFR 43.11).
(f) 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.
(g) An alternative method of compliance or adjustment of the
compliance times that provides an equivalent level of safety may be
approved by the Manager, Wichita Aircraft Certification Office, 1801
Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas
67209. The request shall be forwarded through an appropriate FAA
Maintenance Inspector, who may add comments and then send it to the
Manager, Wichita Aircraft Certification Office.
Note 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita Aircraft Certification Office.
(h) The hose check and replacement required by this AD shall be
done in accordance with the following applicable service bulletins:
--REIMS/CESSNA Service Bulletin (SB) CAB96-21, dated October 18,
1996; Model Affected: F406
--Cessna Aircraft Company SB CQB96-3, dated October 18, 1996; Model
Affected: 425
--Cessna Aircraft Company SB SEB96-15, dated October 18, 1996;
Models Affected: 150, 150A, 150B, 150C, 150D, 150E, 150F, 150G,
150H, 150J, 150K, 150L, 150M, A150K, A150L, A150M, F150F, F150G,
F150H, F150J, F150K, F150L, F150M, FA150K, FA150L, FRA150L, FRA150M,
152, A152, F152, FA152, 172, 172A, 172B, 172C, 172D, 172E, 172F,
172G, 172H, 172I, 172K, 172L, 172M, 172N, 172P, 172Q, FP172, F172D,
F172E, F172F, F172G, F172H, F172K, F172L, F172M, F172N, F172P,
FR172E, FR172F, FR172G, FR172H, FR172J, FR172K, 175, 175A, 175B,
175C, P172D, R172E(T41), R172F(T41), R172G(T41), R172H(T41), R172J,
R172K, 172RG, 177, 177A, 177B, 177RG, F177RG, 180, 180A, 180B, 180C,
180D, 180E, 180F, 180G, 180H, 180J, 180K, 182, 182A, 182B, 182C,
182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P,
182Q, 182R, F182P, F182Q, FR182, R182, T182, TR182, 185, 185A, 185B,
185C, 185D, 185E, A185E, A185F, 188, 188A, 188B, A188, A188A, A188B,
T188C, 206, U206, U206A, U206B, U206C, U206D, U206E, U206F, U206G,
TU206A, TU206B, TU206C, TU206D, TU206E, TU206F, TU206G, P206A,
P206B, P206C, P206D, P206E, TP206, TP206A, TP206B, TP206C, TP206D,
TP206E, 207, 207A, T207, T207A, 210, 210-5 (205), 210-5A, (205A),
210A, 210B, 210C, 210D, 210E, 210F, 210G, 210H, 210J, 210K, 210L,
210M, 210N, 210R, P210N, P210R, and T210F.
--Cessna Aircraft Company SB CAB96-15, Revision 1, October 18, 1996;
Models Affected: 208 and 208B.
--Cessna Aircraft Company SB MEB96-10, dated October 18, 1996;
Models Affected: T303, 310P, 310Q, 310R, T310P, 310Q, 310R, 335,
336, 337, 337A, 337B, 337C, 337D, 337E, 337F, 337G, 337H, F337E,
F337F, F337G, F337H, FT337E, FT337F, FT337GP, FT337HP, FTB337,
T337B, T337C, T337D, T337E, T337F, T337G, T337H, T337H-SP, M337B,
P337H, 340, 340A, 401, 401A, 401B, 402, 402A, 402B, 402C, 404, 411,
411A, 414, 414A, 421, 421A, 421B, and 421C.
This incorporation by reference was approved by the Director of
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Copies may be obtained from Cessna Aircraft Company,
Product Support, P.O. Box 7706, Wichita, Kansas 67277. Copies may be
inspected at the FAA, Central Region, Office of the Assistant Chief
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
(i) This amendment (39-9884) becomes effective on February 3,
1997.
Issued in Kansas City, Missouri, on January 7, 1997.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-815 Filed 1-21-97; 8:45 am]
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