Federal Register / Vol. 60, No. 66 / Thursday, April 6, 1995 / Proposed Rules 17487

§ 981.70 Records and verification.

Each handler shall keep records

which will clearly show the details of

his or her receipts of almonds,

withholdings, sales, shipments,

inventories, reserve disposition,

advertising and promotion activities, as

well as other pertinent information

regarding his or her operation pursuant

to the provisions of this part: Provided,

that, such records shall be kept in the

State of California. * * *

23. A new § 981.76 is added before

the undesignated center heading

‘‘Expenses and Assessments’’ to read as

follows:

§ 981.76 Handler List of Growers.

No later than December 31 of each

crop year, each handler other than a

cooperative handler (hereinafter,

referred to as independent handler)

governed by this subpart shall, upon

request, submit to the Board a complete

list of growers who have delivered

almonds to such independent handler

during that crop year.

24. Section 981.81 is amended by

adding a new paragraph (e) to read as

follows:

§ 981.81 Assessment.

* * * * *

(e) Any assessment not paid by a

handler within a period of time

prescribed by the Board may be subject

to an interest or late payment charge or

both. The period of time, rate of interest

and late payment charge shall be as

recommended by the Board and

approved by the Secretary. Subsequent

to such approval, all assessments not

paid within the prescribed period of

time shall be subject to an interest or

late payment charge or both.

25. Section 981.90 is amended

redesignating paragraph (b)(2) and (b)(3)

as paragraphs (b)(3) and (b)(4) and by

amending newly designated paragraph

(b)(3) by removing the date ‘‘June 1’’ and

adding in its place ‘‘July 1’’ and adding

a new (b)(2), to read as follows:

§ 981.90 Effective time, suspension, or

termination.

* * * * *

(b) * * *

(2) The Secretary shall conduct a

referendum as soon as practical after the

end of the fiscal year ending two years

after implementation of this

amendment, and at such time every fifth

year thereafter, to ascertain whether

continuation of the order is favored by

growers who have been engaged in the

production of almonds for market

within the State of California during the

current crop year.

* * * * *

§ 981.467 [Amended]

26. In § 981.467, paragraph (a) is

amended by removing the date ‘‘July 1’’

and adding in its place ‘‘August 1’’ and

by removing the words ‘‘export or’’ and

‘‘or both,’’ from the second sentence in

paragraph (a).

§ 981.462 [Amended]

27. In § 981.472, paragraph (a) is

amended by removing the dates ‘‘July 1

to August 31’’ and adding in its place

‘‘August 1 to August 31.’’

Dated: March 22, 1995.

Lon Hatamiya,

Administrator.

[FR Doc. 95–8205 Filed 4–5–95; 8:45 am]

BILLING CODE 3410–02–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–ANE–10]

Airworthiness Directives; General

Electric Company CF6 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

General Electric Company (GE) CF6–45/

–50 series turbofan engines. This

proposal would require an initial and

repetitive on-wing visual inspection of

the side links of the five-link forward

mount assembly for cracks, and

replacement of the side links and pylon

attachment bolts, and inspection of the

fail-safe bolt and platform lug, if the

side links are found cracked. This

proposal would also require a shoplevel refurbishment of the side links as

a terminating action to the on-wing

inspection program. This proposal is

prompted by four reports of cracked

side links detected during routine

engine shop visits. The actions specified

by the proposed AD are intended to

prevent a side link fracture, which

could result in the failure of the second

side link, or the forward engine mount

pylon attachment bolts, and possible

separation of the engine from the

aircraft.

DATES: Comments must be received by

May 8, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

95–ANE–10, 12 New England Executive

Park, Burlington, MA 01803–5299.

Comments may be inspected at this

location between 8:00 a.m. and 4:30

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

General Electric Aircraft Engines, CF6

Distribution Clerk, Room 132, 111

Merchant Street, Cincinnati, OH 45246.

This information may be examined at

the FAA, New England Region, Office of

the Assistant Chief Counsel, 12 New

England Executive Park, Burlington MA.

FOR FURTHER INFORMATION CONTACT:

Robert J. Ganley, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7138;

fax (617) 238–7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications

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, specified

above, will be considered before taking

action on the proposed rule. The

proposals contained in this notice may

be changed in light of the comments

received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 95–ANE–10.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, New England Region, Office of the
17488 Federal Register / Vol. 60, No. 66 / Thursday, April 6, 1995 / Proposed Rules

Assistant Chief Counsel, Attention:

Rules Docket No. 95–ANE–10, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

This proposed airworthiness directive

(AD) is applicable to the General

Electric Company (GE) CF6–45/–50

series turbofan engines. The Federal

Aviation Administration (FAA) has

received four reports of cracked side

links of the five-link forward mount

assembly. These cracks were detected

during routine engine shop visits.

Metallurgical analysis performed on the

fractured side links indicate that the

cracking is the result of stress corrosion.

Stress corrosion cracking occurs when

the protective coating is locally missing,

allowing corrosive materials to come in

contact with the base material of the

side link. Preliminary analysis

conducted with a simulated side link

failure indicates that the second side

link, or the pylon attachment bolts

depending on the type of aircraft, may

not be capable of withstanding the

resulting loads in this configuration. A

shop-level refurbishment procedure

exists which enhances the durability of

the side links’ protective coating,

therefore reducing the chance of cracks

due to stress corrosion. This condition,

if not corrected, could result in a side

link fracture, which could result in the

failure of the second side link or the

forward engine mount pylon attachment

bolts, and possible separation of the

engine from the aircraft. The

requirements of this AD have been

reviewed by the Transport Airplane

Directorate.

The FAA has reviewed and approved

the technical contents of GE Aircraft

Engines CF6–50 Service Bulletin No.

72–1092, dated November 18, 1994, that

describes procedures for the initial and

repetitive on-wing visual inspection and

side link refurbishment.

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

require an initial and repetitive on-wing

visual inspection of the side links of the

five-link forward mount assembly for

cracks, replacement of the side links

and pylon attachment bolts, and

inspection of the fail-safe bolt and

platform lug, if side links are found

cracked. This proposal would also

require a shop-level refurbishment of

the side links as a terminating action to

the on-wing inspection program.

The FAA estimates that 220 engines

installed on aircraft of U.S. registry

would be affected by this proposed AD,

that it would take approximately 7.5

work hours per engine to accomplish

the proposed actions, and that the

average labor rate is $60 per work hour.

The FAA has estimated that only a

small percentage of parts will actually

require replacement as a result of this

AD, and therefore, has determined the

parts cost to be negligible. Based on

these figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $99,000.

The regulations proposed herein

would not have substantial direct effects

on the States, on the relationship

between the national government and

the States, or on the distribution of

power and responsibilities among the

various levels of government. Therefore,

in accordance with Executive Order

12612, it is determined that this

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

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

promulgated, will not have a significant

economic impact, positive or negative,

on a substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 14

CFR part 39 of the Federal Aviation

Regulations (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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

General Electric Company: Docket No. 95–

ANE–10.

Applicability: General Electric Company

(GE) CF6–45/–50 series turbofan engines

installed on, but not limited to, Airbus A300

series, Boeing 747 series, and McDonnell

Douglas DC–10 series aircraft.

Note: This AD applies to each engine

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

engines that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (d) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any engine from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent a side link fracture, which

could result in failure of the second side link,

or the forward engine mount pylon

attachment bolts, and possible separation of

the engine from the aircraft, accomplish the

following:

(a) Inspect left-hand side links, Part

Numbers (P/N) 9204M94P01, 9204M94P03,

and 9346M99P01, and right-hand side links,

P/N’s 9204M94P02, 9204M94P04, and

9346M99P02, that have not had the side link

refurbishment done in accordance with GE

CF6–50 Task Numbered Shop Manual, GEK

50481, Chapter 72–23–11, including

Temporary Revision No. 72–0821 and 72–

0822, both dated November 1, 1994, as

follows:

(1) For side links that have not been

previously inspected in accordance with GE

Aircraft Engines (GEAE) CF6–50 Service

Bulletin (SB) No. 72–1092, dated November

18, 1994, inspect in accordance with

paragraph 2.A of GEAE CF6–50 SB No. 72–

1092, dated November 18, 1994, prior to

accumulating 350 cycles in service (CIS), or

750 hours time in service (TIS), after the

effective date of this AD, whichever occurs

earlier.

(2) For side links that have been previously

inspected in accordance with GEAE CF6–50

SB No. 72–1092, dated November 18, 1994,

inspect in accordance with paragraph 2.A of

GEAE CF6–50 SB No. 72–1092, dated

November 18, 1994, prior to accumulating

350 CIS, or 750 hours TIS since inspected in

accordance with GEAE CF6–50 SB No. 72–

1092, dated November 18, 1994, whichever

occurs earlier.

(3) Thereafter, inspect in accordance with

paragraph 2.A of GEAE CF6–50 SB No. 72–

1092, dated November 18, 1994, at intervals
Federal Register / Vol. 60, No. 66 / Thursday, April 6, 1995 / Proposed Rules 17489

not to exceed 350 CIS, or 750 hours TIS since

the last inspection, whichever occurs earlier.

(4) If side links are found cracked, replace

the cracked side links and pylon attachment

bolts with serviceable parts, and inspect the

fail-safe bolt and platform lug in accordance

with paragraph 2.B of GEAE CF6–50 SB No.

72–1092, dated November 18, 1994, prior to

further flight.

(b) Refurbish the left-hand and right-hand

side links identified in paragraph (a) of this

AD at the next engine shop visit after the

effective date of this AD in accordance with

paragraph 2.C of GEAE CF6–50 SB No. 72–

1092, dated November 18, 1994.

Refurbishment of side links in accordance

with this paragraph constitutes terminating

action to the on-wing inspection

requirements of paragraph (a) of this AD.

(c) For the purpose of this AD, an engine

shop visit is defined as the induction of an

engine into a shop for maintenance involving

the separation of the fan and core modules.

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Engine

Certification Office. The request should be

forwarded through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note: Information concerning the existence

of approved alternate methods of compliance

with this airworthiness directive, if any, may

be obtained from the Engine Certification

Office.

Issued in Burlington, Massachusetts, on

March 22, 1995.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 95–8444 Filed 4–3–95; 1:31 pm]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 95–NM–20–AD]

Airworthiness Directives; McDonnell

Douglas Model DC–9 and Model DC–9–

80 Series Airplanes; Model MD–88

Airplanes; and C–9 (Military) Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to certain

McDonnell Douglas Model DC–9 and

Model DC–9–80 series airplanes; Model

MD–88 airplanes; and C–9 (military)

series airplanes; that currently requires

visual and eddy current inspections to

detect cracking of the rudder pedals

adjuster hub assembly, and replacement

of the assembly, if necessary. That AD

was prompted by several occurrences of

failure of the rudder pedals adjuster hub

assembly due to broken detent lugs.

This action would expand the

applicability of the existing AD to

include additional airplanes. The

actions specified by the proposed AD

are intended to prevent loss of rudder

pedals control and reduction of braking

capability.

DATES: Comments must be received by

May 15, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 95–NM–

20–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

McDonnell Douglas Corporation, P.O.

Box 1771, Long Beach, California

90801–1771, Attention: Business Unit

Manager, Technical Administrative

Support, Dept. LS1, M.C. 2–98. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Transport

Airplane Directorate, Los Angeles

Aircraft Certification Office, 3960

Paramount Boulevard, Lakewood,

California.

FOR FURTHER INFORMATION CONTACT:

Augusto Coo, Aerospace Engineer,

Airframe Branch, ANM–120L, FAA,

Transport Airplane Directorate, Los

Angeles Aircraft Certification Office,

3960 Paramount Boulevard, Lakewood,

California 90712; telephone (310) 627–

5225; fax (310) 627–5210.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 95–NM–20–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

95–NM–20–AD, 1601 Lind Avenue SW.,

Renton, Washington 98055–4056.

Discussion

On December 9, 1992, the FAA issued

AD 92–27–07, amendment 39–8441 (57

FR 60116, December 18, 1992),

applicable to certain McDonnell

Douglas Model DC–9 and Model DC–9–

80 series airplanes; Model MD–88

airplanes; and C–9 (military) series

airplanes. That AD requires visual and

eddy current inspections to detect

cracking of the rudder pedals adjuster

hub assembly, and replacement of the

assembly, if necessary. That action was

prompted by several occurrences of

failure of the rudder pedals adjuster hub

assembly due to broken detent lugs. The

actions required by that AD are

intended to prevent loss of rudder

pedals control and reduction of braking

capability.

Since the issuance of AD 92–27–07,

the manufacturer has advised the FAA

that several additional airplanes have

been identified that are subject to the

same type of cracking of the rudder

pedals adjust hub assembly as

addressed by that AD. These airplanes

were inadvertently omitted from the

effectivity listing of McDonnell Douglas

DC–9 Alert Service Bulletin A27–235,

Revision 1, dated February 3, 1992. AD

92–27–07 referenced that specific listing

of airplanes as those subject to the

requirements of that AD. In light of this,

the FAA has determined that those

additional airplanes are subject to the

same unsafe condition addressed by AD

92–27–07.

The FAA has reviewed and approved

McDonnell DC–9 Alert Service Bulletin

A27–325, Revision 2, dated January 27,

1994. This revised service bulletin is

essentially identical to the original

version, which was cited in AD 92–27–

07 as the appropriate source of service