3200 Federal Register / Vol. 62, No. 14 / Wednesday, January 22, 1997 / Rules and Regulations

Subpart O—Civil Money Penalty

Inflation Adjustments

§ 19.240 Inflation adjustments.

The maximum amount of each civil

money penalty within the OCC’s

jurisdiction is adjusted in accordance

with the Federal Civil Penalties

Inflation Adjustment Act of 1990 (28

U.S.C. 2461 note) as follows:

U.S. code citation Description Adjusted maximum penalty

12 U.S.C. 93(b), 504, 1817(j)(16), 1818(i)(2), and 1972(2)(F) .................................... Tier 1 ........................................................

Tier 2 ........................................................

Tier 3 ........................................................

5,500

27,500

1,100,000

12 U.S.C. 164 and 3110(c) .......................................................................................... Tier 1 ........................................................

Tier 2 ........................................................

Tier 3 ........................................................

2,000

22,000

1,100,000

12 U.S.C. 1832(c) and 3909(d)(1) ................................................................................ ................................................................... 1,100

12 U.S.C. 1884 ............................................................................................................. ................................................................... 110

12 U.S.C. 3110(a) ........................................................................................................ ................................................................... 27,500

15 U.S.C. 78u–2(b) ...................................................................................................... Tier 1 (natural person) ..............................

Tier 1 (other person) ................................

Tier 2 (natural person) ..............................

Tier 2 (other person) ................................

Tier 3 (natural person) ..............................

Tier 3 (other person) ................................

5,500

55,000

55,000

275,000

110,000

550,000

42 U.S.C. 4012a(f)(5) ................................................................................................... Per violation .............................................. 350

Per year .................................................... 105,000

§ 19.241 Applicability.

The adjustments in § 19.240 apply to

violations that occur after January 22,

1997.

Dated: January 13, 1997.

Eugene A. Ludwig,

Comptroller of the Currency.

[FR Doc. 97–1507 Filed 1–21–97; 8:45 am]

BILLING CODE 4810–33–P

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.

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, MidContinent 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
Federal Register / Vol. 62, No. 14 / Wednesday, January 22, 1997 / Rules and Regulations 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
3202 Federal Register / Vol. 62, No. 14 / Wednesday, January 22, 1997 / Rules and Regulations

(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.

§ 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-inservice 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.

BILLING CODE 4910–13–U
Federal Register / Vol. 62, No. 14 / Wednesday, January 22, 1997 / Rules and Regulations 3203

BILLING CODE 4910–13–C
3204 Federal Register / Vol. 62, No. 14 / Wednesday, January 22, 1997 / Rules and Regulations

(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]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–227–AD; Amendment

39–9888; AD 97–02–04]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, A300–600, A310, and A320

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Airbus Model

A300, A300–600, A310, and A320 series

airplanes, that currently requires an

inspection of the landing gear brakes for

wear, and replacement if the specified

wear limits are not met. That AD also

requires incorporation of the specified

wear limits into the FAA-approved

maintenance inspection program. This

amendment requires that certain wear

limits that are dependent on brake stack

weight be used in conjunction with

specified brake stack weights, and that

maximum allowable brake wear limits

for additional brake units be

incorporated into the FAA-approved

maintenance program. This amendment

is prompted by a report that some

brakes that are subject to the

requirements of the existing AD have

not been removed from service and by

the determination of the maximum

allowable brake wear limits for

additional brake unit part numbers. The

actions specified by this AD are

intended to prevent the loss of brake

effectiveness during a high energy

rejected takeoff.

EFFECTIVE DATE: February 26, 1997.

ADDRESSES: The service information that

pertains to this rulemaking action may

be obtained from Messier Services,

45635 Willow Pond Plaza, Sterling,

Virginia 20164; Allied Signal

Aerospace, Technical Publications,

Dept. 65–70, P.O. Box 52170, Phoenix,

Arizona 85072–2170; or BFGoodrich

Company, Aircraft Evacuation Systems,

Department 7916, Phoenix, Arizona

85040. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

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: Joe

Jacobsen, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,