Federal Register / Vol. 60, No. 44 / Tuesday, March 7, 1995 / Rules and Regulations 12407

category, that have steel wing attachment

assembly bolts and hardware:

Model Serial numbers

34C ...... GP–1 through GP–50.

T–34C .. GL–2 through GL–353.

T–34C–

1.

GM–1 through GM–71 and GM–78

through GM–98.

Compliance: Within whichever of the

following occurs later, unless already

accomplished:

• Four years after airplane manufacture;

• Four years after installing a new wing

attachment assembly; or

• Within the next 30 calendar days after

the effective date of this AD.

To prevent the wing from separating

from the fuselage because of failure of

the wing attachment nut assembly,

accomplish the following:

(a) Replace all eight steel wing attach

bolts and hardware with Inconel bolts

and hardware in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

section in Beech Service Bulletin No.

2487, dated August 19 1993.

Note 1: Replacing all eight steel wing

attach bolts and hardware with Inconel bolts

and hardware as required by this AD

eliminates the repetitive inspection

requirements of AD 85–22–05, Amendment

39–5146, for the affected airplanes.

(b) 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.

(c) An alternative method of compliance or

adjustment of the 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, 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 ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(d) The replacements required by this AD

shall be done in accordance with Beech

Service Bulletin No. 2487, dated August

1993. 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 the Beech Aircraft Corporation, P.O.

Box 85, Wichita, Kansas 67201–0085. 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.

(e) This amendment (39–9162) becomes

effective on April 7, 1995.

Issued in Kansas City, Missouri, on

February 14, 1995.

Barry D. Clements,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 95–4367 Filed 3–6–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–132–AD; Amendment

39–9156; AD 95–04–04]

Airworthiness Directives; British

Aerospace Model Avro 146–RJ70A and

–RJ85A Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain British Aerospace

Model Avro 146–RJ70A and –RJ85A

series airplanes, that requires an

inspection to identify and remove

certain cable terminals on the auxiliary

power unit (APU) starter circuit and

installation of certain new cable

terminals. This amendment is prompted

by a report that, during an inspection of

the cable terminals on the APU starter

circuit, incorrect cable terminals were

found installed on these airplanes. The

actions specified by this AD are

intended to ensure the installation of

correct starter cable terminals in the

APU; incorrect cables could lead to the

inability of the pilot to start the APU

when needed in a situation of loss of

other electrical power sources.

DATES: Effective April 6, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 6,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from British Aerospace Holdings, Inc.,

Avro International Aerospace Division,

P.O. Box 16039, Dulles International

Airport, Washington DC 20041–6039.

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:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2148; fax (206) 227–1320.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain British

Aerospace Model Avro 146–RJ70A and

–RJ85A series airplanes was published

in the Federal Register on November 7,

1994 (59 FR 55383). That action

proposed to require a detailed visual

inspection to identify the cable

terminals fitted to cables KA47 and

KA48 on the APU starter circuit at

terminal block KA9, removal of certain

cable terminals, and installation of

certain new cable terminals.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.

As a result of recent communications

with the Air Transport Association

(ATA) of America, the FAA has learned

that, in general, some operators may

misunderstand the legal effect of AD’s

on airplanes that are identified in the

applicability provision of the AD, but

that have been altered or repaired in the

area addressed by the AD. The FAA

points out that all airplanes identified in

the applicability provision of an AD are

legally subject to the AD. If an airplane

has been altered or repaired in the

affected area in such a way as to affect

compliance with the AD, the owner or

operator is required to obtain FAA

approval for an alternative method of

compliance with the AD, in accordance

with the paragraph of each AD that

provides for such approvals. A note has

been added to this final rule to clarify

this requirement.

The FAA has recently reviewed the

figures it has used over the past several

years in calculating the economic

impact of AD activity. In order to

account for various inflationary costs in

the airline industry, the FAA has

determined that it is necessary to

increase the labor rate used in these

calculations from $55 per work hour to

$60 per work hour. The economic

impact information, below, has been

revised to reflect this increase in the

specified hourly labor rate.

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.
12408 Federal Register / Vol. 60, No. 44 / Tuesday, March 7, 1995 / Rules and Regulations

The FAA estimates that 3 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 1.5 work

hours per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour.

Required parts will cost approximately

$250 per airplane. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$1,020, or $340 per airplane.

The total cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

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. 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:

95–04–04 British Aerospace Regional

Aircraft Limited, Avro International

Aerospace Division (Formerly British

Aerospace, PLC; British Aerospace

Commercial Aircraft Limited):

Amendment 39–9156. Docket 94–NM–

132–AD.

Applicability: Model Avro 146–RJ70A and

–RJ85A airplanes, as listed in Avro

International Aerospace Service Bulletin 49–

40, Revision 1, dated March 17, 1994;

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 use the authority

provided in paragraph (b) 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 airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent loss of electrical power to the

auxiliary power unit (APU), accomplish the

following:

(a) Within 5 months after the effective date

of this AD, perform a detailed visual

inspection to identify the cable terminals

fitted to cables KA47 and KA48 in the APU

starter circuit at terminal block KA9, in

accordance with Avro International

Aerospace Service Bulletin S.B. 49–40,

Revision 1, dated March 17, 1994. If the cable

terminals are identified as part number (P/N)

S1007–042, prior to further flight, remove the

cable terminals and install new cable

terminals having P/N S1006–040, in

accordance with the service bulletin.

(b) 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,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(c) 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.

(d) The inspection, removal, and

installation shall be done in accordance with

Avro International Aerospace Service

Bulletin S.B. 49–40, Revision 1, dated March

17, 1994, which contains the following list of

effective pages:

Page No.

Revision

level

shown on

page

Date shown on

page

1– ................. 1– ............ Mar. 17, 1994.

2–4– ............. Original .... Feb. 16, 1994.

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 British Aerospace Holdings, Inc., Avro

International Aerospace Division, P.O. Box

16039, Dulles International Airport,

Washington DC 20041–6039. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(e) This amendment becomes effective on

April 6, 1995.

Issued in Renton, Washington, on February

15, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–4255 Filed 3–6–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–CE–10–AD; Amendment 39–

9161; AD 95–04–09]

Airworthiness Directives; Pilatus

Britten-Norman BN2A, BN2B, and

BN2T Islander Series and BN2A Mk III

Trislander Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to Pilatus Britten-Norman

BN2A, BN2B, and BN2T Islander and

BN2A Mk III Trislander series airplanes

that are equipped with a nose wheel

steering disconnect system with either a

Modification NB/M/503 or Modification

NB/M/733 nose undercarriage unit. This

action requires repetitively inspecting

the nose wheel steering drive ring for

cracks, and replacing any cracked drive

ring. A report of the rudder pedals

jamming in the central position during

takeoff on one of the affected airplanes

prompted this action. The actions

specified by this AD are intended to