Federal Register / Vol. 61, No. 117 / Monday, June 17, 1996 / Rules and Regulations 30501

at that time. In addition, the Council

agrees to forgo any late fee charges and

interest for the duration of the

postponement of the payment of

assessments.

After consideration of all relevant

material presented, it is found that this

regulation, as set forth herein, tends to

effectuate the declared policy of the Act.

Pursuant to 5 U.S.C. 553, it is also

found and determined that good cause

exists for not postponing the effective

date of this action until 30 days after

publication in the Federal Register

because: (1) This rule establishes rules

and regulations in accordance with the

provisions of the Act; (2) the Council

has received requests for the

postponement of the payment of

assessments and needs rules to

administer the postponement process;

and (3) no useful purpose will be served

in delaying the effective date until 30

days after publication of this final rule.

List of Subjects in 7 CFR Part 1208

Administrative practice and

procedure, Advertising, Consumer

information, Marketing agreements, Cut

flowers, Cut greens, Promotion,

Reporting and recordkeeping

requirements.

For the reasons set forth in the

preamble, 7 CFR Part 1208 is amended

as follows:

PART 1208—FRESH CUT FLOWERS

AND FRESH CUT GREENS

PROMOTION AND INFORMATION

ORDER

1. The authority citation for 7 CFR

Part 1208 continues to read as follows:

Authority: 7 U.S.C. 6801 et seq.

2. In Part 1208 a new Subpart B is

added to read as follows:

Subpart B—Rules and Regulations

Definitions

Sec.

1208.100 Terms defined.

Assessments

1208.150 Procedures for postponement of

assessments.

Subpart B—Rules and Regulations

Definitions

§ 1208.100 Terms defined.

Unless otherwise defined in this

subpart, definitions or terms used in

this subpart shall have the same

meaning as the definitions of such terms

which appear in Subpart A—Fresh Cut

Flowers and Fresh Cut Greens

Promotion and Information Order of this

part.

Assessments

§ 1208.150 Procedures for postponement

of collections.

(a) For a request for postponement of

the payment of assessments to be

granted, the qualified handler

requesting such postponement must:

Submit a written opinion from a

Certified Public Accountant stating that

the handler making the request is

insolvent or will be unable to continue

to operate if the handler is required to

pay the assessments when due; and

submit copies of the handler’s last three

(3) years’ federal tax returns. The

request must be in writing no later than

30 days after the assessment for the first

month of the requested postponement

period is due. Applications postmarked

after the 30-day due date will not be

considered by the Council. The

qualified handler must file handler

reports with the Council for each month

during the postponement period. The

postponement period may not exceed

six (6) months unless an extension is

requested and granted by the Council.

Only one extension of up to six (6)

months may be granted. Within the

postponement period, the qualified

handler will be exempt from paying

assessments beginning with the first

month for which the request for

postponement is filed with the Council

and for no more than six (6) months

unless an extension is granted. The

same procedures used for the initial

request will be used to grant any

extension. The written request must

specify:

(1) a reason for the request;

(2) detailed information concerning

the qualified handler’s name, address,

and telephone and fax numbers;

(3) the month(s) for which the request

is made;

(4) assessments due per month or

gross sales per month;

(5) total assessments due;

(6) the percent or amount of the

outstanding assessment to be paid each

month after the postponement of

payment is granted; and

(7) the starting and ending date for the

payment of assessments due.

(b) At the end of the postponement

period, the qualified handler must pay

the percent or amount outstanding of

assessments agreed upon each month as

well as any other assessments which are

due. An extension of time for payment

of postponed assessments, if granted,

will be for the same months previously

requested and granted. The extension

must not exceed six (6) months. If a

qualified handler requests that another

period be postponed, that handler must

file another application for the

postponement of the assessment for the

second period using the same procedure

which was followed in requesting the

first postponement. A qualified handler

may request the postponement of the

payment of assessments for a maximum

of two periods of up to six (6) months

each. The payment applicable to the

second postponement period, if granted,

may not be extended, and the payment

period must not exceed the length of the

postponement period. Payment of the

total assessments due, when an

extension and a second period are

granted, must begin within one (1) year

after the first postponed month’s

assessments were originally due. No

additional postponements would be

considered by the Council until the

assessments owed for the first two

periods have been paid. The Council

may conduct an audit of the qualified

handler’s records at any time to

determine whether the qualified handler

will be unable to continue to operate if

the handler is required to pay the

assessments due. In the event that

postponed assessments are not paid

when due, the Council can demand that

all such assessments due be paid in

their entirety.

(c) Charges for late payment of

assessments as described in § 1208.52

will not be imposed on assessments for

which postponement of payment has

been granted.

Dated: June 7, 1996.

Robert C. Keeney,

Director, Fruit and Vegetable Division.

[FR Doc. 96–15092 Filed 6–14–96; 8:45 am]

BILLING CODE 3410–02–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93–CE–54–AD; Amendment 39–

9665; AD 96–12– 22]

RIN 2120–AA64

Airworthiness Directives; Cessna

Aircraft Company Engine Oil Filter

Adapter Assemblies Installed on

Aircraft

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to Cessna Aircraft Company

(Cessna) engine oil filter adapter

assemblies installed on aircraft. This

action requires inspecting the oil filter

and adapter assembly (or torque putty,
30502 Federal Register / Vol. 61, No. 117 / Monday, June 17, 1996 / Rules and Regulations

if installed) for oil leakage and proper

installation of the adapter retaining nut

and fretting of associated threads

(security), and replacing any oil filter

adapter assembly with security

problems; applying torque putty

between the engine filter adapter

assembly, nut, and oil pump housing

(unless already equipped with torque

putty); and repetitively inspecting the

torque putty for misalignment, evidence

of oil leakage, or torque putty cracks,

and reinspecting the oil filter and

adapter assembly threads if

misalignment, evidence of oil leakage,

or torque putty cracks are found.

Reports of loose or separated engine oil

filter adapters on several airplanes

prompted this action. The actions

specified by this AD are intended to

prevent loss of engine oil caused by

loose or separated oil filter adapters,

which, if not detected and corrected,

could result in engine stoppage while in

flight and loss of control of the airplane.

EFFECTIVE DATE: July 31, 1996.

ADDRESSES: Information that applies to

this AD may be examined at the Federal

Aviation Administration (FAA), Central

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket 93–

CE–54–AD, Room 1558, 601 E. 12th

Street, Kansas City, Missouri 64106.

FOR FURTHER INFORMATION CONTACT: Mr.

Paul O. Pendleton, Aerospace Engineer,

FAA, Wichita Aircraft Certification

Office, 1801 Airport Road, Room 100,

Wichita, Kansas 67209; telephone (316)

946–4143; facsimile (316) 946–4407.

SUPPLEMENTARY INFORMATION:

Events Leading to the AD

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to include an AD that would

apply to airplanes of any type design

that utilize any Cessna engine oil filter

adapter was published in the Federal

Register on January 22, 1996 (61 FR

1534). The action proposed to require

(1) inspecting the oil filter and adapter

assembly (or torque putty, if installed)

for oil leakage and proper installation of

the adapter retaining nut and fretting of

associated threads (security), and

replacing any oil filter adapter assembly

with security problems; (2) applying

torque putty between the engine filter

adapter assembly, nut, and oil pump

housing (unless already equipped with

torque putty); and (3) repetitively

inspecting the torque putty for

misalignment, evidence of oil leakage,

or torque putty cracks, and reinspecting

the oil filter and adapter assembly

threads if misalignment, evidence of oil

leakage, or torque putty cracks are

found. This proposal revised a previous

proposal that was published in the

Federal Register on September 19, 1994

(59 FR 47821).

Reports of loose or separated engine

oil filter adapters on several airplanes

prompted the proposal.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposed rule or the FAA’s

determination of the cost to the public.

After careful review of all available

information related to the subject

presented above, the FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial corrections. The FAA has

determined that these minor corrections

will not change the meaning of the AD

and will not add any additional burden

upon the public than was already

proposed.

Cost Impact

The FAA estimates that 70,000

airplanes in the U.S. registry incorporate

one of the affected engine oil filter

adapter assemblies and will, therefore,

be affected by this AD; that it will take

approximately 1 workhour per airplane

to accomplish the initial inspection and

torque putty application; and that the

average labor rate is approximately $60

an hour. Based on these figures, the total

cost impact of this AD on U.S. operators

is estimated to be $4,200,000. This

figure is based on the assumption that

no operator has accomplished the initial

inspection, and does not take into

account the cost for the repetitive

inspections. Since the pilot is allowed

to repetitively inspect the torque putty,

the only cost of the repetitive

inspections is the time incurred by the

pilot and the cost of an inspection

required if misalignment, evidence of

oil leakage, or torque putty cracks are

found. The FAA has no way of

determining how many repetitive

inspections each individual operator

will incur over the life of the airplane.

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.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

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 final

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.

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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive

(AD) to read as follows:

96–12–22 Cessna Aircraft Company:

Amendment 39–9665; Docket No. 93–

CE–54–AD.

Applicability: Cessna Engine Oil Filter

Adapters Assemblies, part numbers

0450404–(all dash numbers), 0556004–(all

dash numbers), 0556010–(all dash numbers),

0756023–(all dash numbers), 0756024–(all

dash numbers), 1250403–(all dash numbers),

1250417–(all dash numbers), 1250418–(all

dash numbers), 1250921–(all dash numbers),

and 1250922–(all dash numbers), installed

on, but not limited to, the following:

(1) Cessna Models 100, 200, 300, and 400

Series airplanes (all serial numbers),

certificated in any category, that are

equipped with at least one Teledyne

Continental Motors (TCM) engine.

(2) Airplanes that have an affected full flow

engine oil adapter installed by field approval,

including, but not limited to, the following

model or series airplanes, certificated in any

category:

Manufacturer Series/models

Rockwell/Aero Commander/Meyers.200 Series.

Twin Commander ...... Models 500A and

685.

Beech ........................ 33, 35, 36, and 55

Series.

Piper .......................... PA46 Series.
Federal Register / Vol. 61, No. 117 / Monday, June 17, 1996 / Rules and Regulations 30503

Manufacturer Series/models

Navion ....................... Rangemaster 17 Series.

Wren .......................... Model 460.

Bellanca .................... 260 and 300 Series.

(3) Airplanes equipped with any of the

following Teledyne Continental Motors

model or model series engines:

O–200

TSIO–470

TSIO–520

TSIO–550

O–470

O–520

GTSIO–520

IO–470

IO–520

IO–550

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 (f) 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.

Note 2: This AD does not apply to engine

oil filter adapter assemblies manufactured by

Teledyne Continental Motors (See Figure 1 of

this AD). Compliance: Required initially as

specified in both of the following, and

thereafter as indicated in the body of this AD:

1. Within the next 100 hours time-inservice (TIS) after the effective date of this

AD or when the engine oil filter is removed,

whichever occurs first; and

2. Every time the engine oil filter is

removed.

To prevent loss of engine oil caused by

loose or separated oil filter adapters, which

could result in engine stoppage while in

flight and loss of control of the airplane,

accomplish the following:

(a) For airplanes with engine oil filter

adapter assemblies that do not have torque

putty between the engine filter adapter

assembly, nut, and oil pump housing,

accomplish the following:

(1) Inspect the adapter locking nut

installation for evidence of oil leakage.

(2) Check the torque of the adapter nut

installation and ensure that the torque value

is within the limits of 50 through 60 foot

pounds.

(3) If evidence of oil leakage is found or the

torque is not within the 50 through 60-foot

pound limit, prior to further flight, remove

the adapter and filter assembly, and:

(i) Inspect the threads of the adapter

assembly and engine for signs of damaged or

cracked threads; and

(ii) Replace any adapter assembly and

engine oil pump housing (if necessary) that

have evidence of thread damage or cracks.

(4) Apply torque putty between the engine

filter adapter assembly, nut, and oil pump

housing as specified in Figure 1 of this AD.

(5) Reassemble the engine oil filter

assembly.

BILLING CODE 4910–13–V
30504 Federal Register / Vol. 61, No. 117 / Monday, June 17, 1996 / Rules and Regulations

BILLING CODE 4910–13–C
Federal Register / Vol. 61, No. 117 / Monday, June 17, 1996 / Rules and Regulations 30505

(b) For airplanes with torque putty between

the engine filter adapter assembly, nut, and

oil pump housing, inspect the torque putty

for misalignment, evidence of oil leakage, or

cracks.

(1) If any misalignment, evidence of oil

leakage, or torque putty cracks are found,

prior to further flight, accomplish the

requirements specified in paragraph (a) of

this AD, including all subparagraphs.

(2) If no misalignment, evidence of oil

leakage, or torque putty cracks are found,

reinspect at intervals not to exceed 100 hours

TIS until the engine oil filter is removed.

(c) Replacing the engine oil filter adapter

assembly does not eliminate the repetitive

inspection requirement of this AD.

(d) The repetitive inspections of the torque

putty as required by 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).

(e) 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.

(f) An alternative method of compliance or

adjustment of the initial or repetitive

compliance time that provides an equivalent

level of safety may be approved by the

Manager, Wichita Aircraft Certification Office

(ACO), 1801 Airport Road, Room 100, MidContinent 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 ACO.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(g) Information related to this AD may be

examined at the FAA, Central Region, Office

of the Assistant Chief Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106.

(h) This amendment (39–9665) becomes

effective on July 31, 1996.

Issued in Kansas City, Missouri, on June 3,

1996.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 96–14631 Filed 6–14–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–CE–05–AD; Amendment 39–

9591; AD 96–09–15]

RIN 2120–AA64

Airworthiness Directives; Cessna

Aircraft Company Models 208 and

208B Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This action makes a

correction to Airworthiness Directive

(AD) 96–09–15 concerning all Cessna

Aircraft Company (Cessna) Models 208

and 208B airplanes, which was

published in the Federal Register on

May 7, 1996 (61 FR 20641). That

publication incorrectly references a cue

for the pilot or crew member in severe

icing conditions. The AD currently

requires the pilot to follow certain

visual cues during flight in icing

conditions and the third of these cues

requires the pilot to look at the engine

propeller spinner. This cue is

inappropriate for this type of airplane.

The intent of the AD in paragraph (a)

(1), first bullet, third cue, should not be

a requirement for the Cessna Models

208 and 208B. This action corrects the

AD to reflect this change.

EFFECTIVE DATE: June 11, 1996.

FOR FURTHER INFORMATION CONTACT: Mr.

John Dow, Aerospace Engineer, FAA,

Small Airplane Directorate, 1201

Walnut, suite 900, Kansas City, Missouri

64106; telephone (816) 426–6934;

facsimile (816) 426–2169.

SUPPLEMENTARY INFORMATION: On May 7,

1996, the Federal Aviation

Administration (FAA) issued AD 96–

09–15, Amendment 39–9591 (61 FR

20641, May 7, 1996), which applies to

all Cessna Models 208 and 208B

airplanes. This AD requires a revision in

the Airplane Flight Manual (AFM) by

incorporating a warning into the

Limitations Section of the AFM. Within

this warning (in the first bulleted

paragraph) are cues for the pilot to

follow during flight in severe icing

conditions. The third cue references

accumulation of ice on the engine

propeller spinner.

Need for the Correction

The AD incorrectly references the

‘‘* * * engines propeller spinner

* * *’’ which is not appropriate for the

type design of these Cessna Models 208

and 208B airplanes. These airplanes are

single engine designs which would not

allow the pilot to see the engine

propeller spinner from the cockpit.

Correction of Publication

Accordingly, the publication of May

7, 1996 (61 FR 20641), of Amendment

39–9591; AD 96–09–15, which was the

subject of FR Doc. 96–10729, is

corrected as follows:

§ 39.13 [Corrected]

On page 20642, in the third column,

section 39.13, paragraph (a) (1), line 17

from the top of the column, disregard

and delete ‘‘-Accumulation of ice on the

engine propeller spinner * * *’’.

Action is taken herein to clarify this

requirement of AD 96–09–15 and to add

this AD correction to section 39.13 of

the Federal Aviation Regulations (14

CFR 39.13).

The effective date remains June 11, 1996.

Issued in Kansas City, Missouri on June 10,

1996.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 96–15139 Filed 6–14–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 93–CE–34–AD; Amendment 39–

9670; AD 96–13–02]

RIN 2120–AA64

Airworthiness Directives; Jetstream

Aircraft Limited (Formerly British

Aerospace, Regional Airlines Limited)

Jetstream Model 3201 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Jetstream Aircraft

Limited (JAL) Jetstream Model 3201

airplanes. This action requires

repetitively inspecting the spigot

housing plate for cracks and corrosion at

the wing/fuselage forward attachment

sliding joint, replacing any cracked or

corroded part, and eventually replacing

the spigots and spigot housing plate

with new parts of improved design. A

crack in the spigot housing plate

assembly found during fatigue testing of

the affected airplanes prompted this

action. The actions specified by this AD

are intended to prevent structural

failure of the wing/fuselage area caused

by a cracked or corroded spigot housing

assembly.

DATES: Effective August 7, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 7,

1996.