Federal Register / Vol. 60, No. 37 / Friday, February 24, 1995 / Rules and Regulations 10307

PART 265—RULES REGARDING

DELEGATION OF AUTHORITY

1. The authority citation for Part 265

continues to read as follows:

Authority: 12 U.S.C. 248 (i) and (k).

2. Section 265.6 is amended by

revising paragraph (b)(2) and by adding

paragraph (b)(3) to read as follows:

§ 265.6 Functions delegated to General

Counsel.

* * * * *

(b) * * *

(2) Disclosure to foreign authorities.

To make the determinations required for

disclosure of information to a foreign

bank regulatory or supervisory

authority, and to obtain, to the extent

necessary, the agreement of such

authority to maintain the confidentiality

of such information to the extent

possible under applicable law.

(3) Assistance to foreign authorities.

To approve requests for assistance from

any foreign bank regulatory or

supervisory authority that is conducting

an investigation regarding violations of

any law or regulation relating to banking

matters or currency transactions

administered or enforced by such

authority, and to make the

determinations required for any

investigation or collection of

information and evidence pertinent to

such request. In deciding whether to

approve requests for assistance under

this paragraph, the General Counsel

shall consider:

(i) Whether the requesting authority

has agreed to provide reciprocal

assistance with respect to banking

matters within the jurisdiction of any

appropriate Federal banking agency;

(ii) Whether compliance with the

request would prejudice the public

interest of the United States; and

(iii) Whether the request is consistent

with the requirement that the Board

conduct any such investigation in

compliance with the laws of the United

States and the policies and procedures

of the Board.

* * * * *

By order of the Board of Governors of the

Federal Reserve System, February 17, 1995.

William W. Wiles,

Secretary of the Board.

[FR Doc. 95–4547 Filed 2–23–95; 8:45 am]

BILLING CODE 6210–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93–CE–41–AD; Amendment 39–

9136; AD 95–02–18]

Airworthiness Directives; Beech

Aircraft Corporation Models 1900,

1900C, and 1900D Airplanes;

Correction

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This action makes a

correction to Airworthiness Directive

(AD) 95–02–18 concerning Beech

Aircraft Corporation Models 1900,

1900C, and 1900D airplanes, which was

published in the Federal Register on

February 3, 1995 (60 FR 6652). That

publication inadvertently referenced an

incorrect repetitive inspection interval

for Models 1900 and 1900C airplanes

with a part number 129–910032–79

engine truss installed. The inspection

interval in sections B and C of the

engine truss should be 3,000 hours timein-service (TIS) instead of 100 hours

TIS. This action corrects the AD to

reflect this repetitive inspection

interval.

EFFECTIVE DATE: March 25, 1995.

FOR FURTHER INFORMATION CONTACT: Mr.

Steven E. Potter, Wichita Aircraft

Certification Office, FAA, 1801 Airport

Road, Mid-Continent Airport, Wichita,

Kansas 67209; telephone (316) 946–

4124; facsimile (316) 946–4407.

SUPPLEMENTARY INFORMATION: On

January 26, 1995, the Federal Aviation

Administration (FAA) issued AD 95–

02–18, Amendment 39–9136 (60 FR

6652, February 3, 1995), which applies

to Beech Models 1900, 1900C, and

1900D airplanes. This AD supersedes

AD 92–06–09, Amendment 39–8189,

with a new AD that requires repetitively

inspecting the engine trusses for cracks,

repairing or replacing any cracked

engine truss, and installing

reinforcement doublers on certain

airplanes.

The AD inadvertently references an

incorrect repetitive inspection interval

for Beech Models 1900 and 1900C

airplanes with a part number 129–

910032–79 engine truss installed. The

inspection interval in sections B and C

of the engine truss should be 3,000

hours TIS instead of 100 hours TIS. This

action corrects the AD to reflect this

repetitive inspection interval.

Need for Correction

As published, the final regulations

have incorrectly referenced the

repetitive inspection interval for Beech

Models 1900 and 1900C airplanes with

a part number 129–910032–79 engine

truss installed. The way the final

regulations are currently written will

make operators repetitively inspect

Sections B and C of the engine truss

more often than was intended or

proposed in the notice of proposed

rulemaking.

Correction of Publication

Accordingly, the publication of

February 3, 1995 (60 FR 6652) of

Amendment 39–9136; AD 95–02–18,

which was the subject of FR Doc. 94–

2403, is corrected as follows:

§ 39.13 [Corrected]

On page 6653, in paragraph (b), in the

Chart that spreads across all three

columns, change the second entry in the

Repetitive Inspection column from

‘‘Every 100 hours TIS.’’ to ‘‘Every 3,000

hours TIS.’’ The chart will now read as

follows:

Models

Area specified in figure 1 of Beech SB

No. 2255, rev. VI

Initial inspection Repetitive inspection

1900 and 1900C ................................................... A ................................ Upon accumulating 1,400 hours TIS* ....... Every 100 hours TIS.

1900 and 1900C ................................................... B and C ..................... Upon accumulating 3,200 hours TIS* ....... Every 3,000 hours TIS.

1900D ................................................................... A ................................ Upon accumulating 3,200 hours TIS* ....... Every 450 hours TIS.

1900D ................................................................... B and C ..................... Upon accumulating 3,200 hours TIS* ....... Every 3,000 hours TIS

* Or within the next 100 hours TIS after the effective date of this AD, whichever occurs later.
10308 Federal Register / Vol. 60, No. 37 / Friday, February 24, 1995 / Rules and Regulations

Issued in Kansas City, Missouri, on

February 15, 1995.

Barry D. Clements,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 95–4371 Filed 2–23–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–ANE–57; Amendment 39–

9150; AD 95–03–14]

Airworthiness Directives; Teledyne

Continental Motors IO–346, IO–520,

and IO–550 Series Reciprocating

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Teledyne

Continental Motors (TCM) IO–346, IO–

520, and IO–550 series reciprocating

engines, that currently requires initial

and repetitive inspections of the engine

mount brackets for cracks, and if found

cracked, replacement with improved

design engine mount brackets. All

engine mount brackets require

replacement with improved design

engine mount brackets at the next

engine removal after the effective date of

that airworthiness directive (AD). This

amendment clarifies the identification

procedures to determine which engine

mount brackets must be inspected. This

amendment is prompted by reports that

the engine mount bracket part numbers,

which are ink stamped, can be easily

obliterated. The actions specified by this

AD are intended to prevent engine

separation from the aircraft due to

cracks in the engine mount brackets.

DATES: Effective March 13, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 13,

1995.

Comments for inclusion in the Rules

Docket must be received on or before

April 25, 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.

94–ANE–57, 12 New England Executive

Park, Burlington, MA 01803–5299.

The service information referenced in

this AD may be obtained from Teledyne

Continental Motors, P.O. Box 90,

Mobile, AL 36601; telephone (334) 438–

3411. This information may be

examined at the FAA, New England

Region, Office of the Assistant Chief

Counsel, Burlington, MA; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Jerry

Robinette, Aerospace Engineer, Atlanta

Aircraft Certification Office, FAA, Small

Airplane Directorate, Campus Building,

1701 Columbia Ave., Suite 2–160,

College Park, GA 30337–2748;

telephone (404) 305–7371, fax (404)

305–7348.

SUPPLEMENTARY INFORMATION: On April

19, 1994, the Federal Aviation

Administration (FAA) issued

airworthiness directive (AD) 94–09–07,

Amendment 39–8896 (59 FR 23148,

May 5, 1994), applicable to certain

Teledyne Continental Motors (TCM) IO–

346, IO–520, and IO–550 series

reciprocating engines, to require initial

and repetitive dye penetrant inspections

for cracks in certain lower left engine

mount brackets, Part Number (P/N)

630695. If the lower left engine mount

bracket is found cracked, that AD

requires replacing both the lower left

and lower right engine mount brackets

with improved design engine mount

brackets, P/N 653306 and 653305,

respectively. If a crack is not detected,

the lower left engine mount bracket

requires repetitive inspections at

intervals not to exceed 500 hours time

in service (TIS) until the next engine

removal, at which time engine mount

brackets, P/N 630694 and 630695, are

replaced with improved design engine

mount brackets, P/N 653306 and

653305. Installation of these improved

design engine mount brackets

constitutes terminating action to the

inspection requirements of that AD.

That action was prompted by reports of

cracks in engine mount brackets on

engines that have completed at least one

overhaul cycle. That condition, if not

corrected, could result in engine

separation from the aircraft due to

cracks in the engine mount brackets.

Since the issuance of that AD, the

FAA has received reports of difficulty in

identifying the engine mount brackets

that must be inspected. The P/N is inkstamped on the part and is quite easily

obliterated. The problem arises when

the Casting Number (C/N), which is

different from the P/N, is mistaken for

the P/N, and the AD is incorrectly

believed to not apply.

The FAA has reviewed and approved

the technical contents of TCM

Mandatory Service Bulletin (MSB) No.

MSB94–9, dated October 21, 1994, that

provides positive identification of

affected engine mount brackets that

require inspection, and replacement, if

necessary.

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of this same

type design, this AD supersedes AD 94–

09–07 to clarify the identification

procedures to determine which engine

mount brackets must be inspected. The

actions are required to be accomplished

in accordance with the MSB described

previously.

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public 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

under the caption ADDRESSES. 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 Number 94–ANE–57.’’ The

postcard will be date stamped and

returned to the commenter.

The regulations adopted herein will

not have substantial direct effects on the

States, on the relationship between the