[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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[[Page 3203]]

[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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