Federal Register / Vol. 60, No. 32 / Thursday, February 16, 1995 / Rules and Regulations 8929

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 and replacement shall

be done in accordance with Fokker Service

Bulletin SBF100–57–018, dated September

23, 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 Fokker Aircraft USA, Inc., 1199 North

Fairfax Street, Alexandria, Virginia 22314.

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

March 20, 1995.

Issued in Renton, Washington, on February

3, 1995.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–3247 Filed 2–15–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–109–AD; Amendment

39–9141; AD 95–03–04]

Airworthiness Directives; British

Aerospace Model Viscount 744, 745D,

and 810 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all British Aerospace

Model Viscount 744, 745D, and 810

series airplanes, that requires repetitive

inspections to detect fatigue cracking in

the pivot pins that attach both nose

wheel steering actuators to the steering

head assembly, and replacement of

cracked pins. This amendment is

prompted by a reported failure of a

pivot pin due to fatigue cracking. The

actions specified by this AD are

intended to prevent failure of the pivot

pin, which could result in the loss of

nose wheel steering capability.

DATES: Effective March 20, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 20,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from British Aerospace Regional

Aircraft Ltd., Engineering Support

Manager, Military Business Unit,

Chadderton Works, Greengate,

Middleton, Manchester M24 1SA,

England. 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 all British

Aerospace Model Viscount 744, 745D,

and 810 series airplanes was published

in the Federal Register on November 14,

1994 (59 FR 56435). That action

proposed to require initial and

repetitive magnetic particle inspections

to detect cracking of the pivot pin that

attaches the nose wheel steering

actuators to the steering head assembly,

and replacement of cracked pins.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

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 determined that this

addition will neither increase the

economic burden on any operator nor

increase the scope of the AD.

The FAA estimates that 29 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 3

work hours per airplane, per inspection

cycle, to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$5,220, or $180 per airplane, per

inspection cycle.

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:
8930 Federal Register / Vol. 60, No. 32 / Thursday, February 16, 1995 / Rules and Regulations

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:

95–03–04 British Aerospace Regional

Aircraft Limited (Formerly British

Aerospace Commercial Aircraft Limited,

Vickers-Armstrongs Aircraft Limited):

Amendment 39–9141. Docket 94–NM–

109–AD.

Applicability: All Model Viscount 744,

745D, and 810 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 use the authority

provided in paragraph (c) 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 nose wheel steering

capability due to failure of the pivot pin,

accomplish the following:

(a) Prior to the accumulation of 1,100

landings after the effective date of this AD,

or within 14 months after the effective date

of this AD, whichever occurs first, perform a

magnetic particle inspection to detect cracks

of the nose wheel steering actuators

connecting (pivot) pins, in accordance with

either Viscount Preliminary Technical Leaflet

(PTL) 334, Issue 2, dated July 8, 1992 (for

Model 744 and 745D series airplanes); or

Viscount PTL 205, Issue 2, dated July 8, 1992

(for Model 810 series airplanes); as

applicable. Repeat this inspection thereafter

at intervals not to exceed 1,100 landings or

14 months, whichever occurs first.

(b) If any crack is found in a pivot pin

during any inspection required by this AD,

replace the pivot pin in accordance with

either Preliminary Technical Leaflet (PTL)

334, Issue 2, dated July 8, 1992 (for Model

744 and 745D series airplanes), or Viscount

PTL 205, Issue 2, dated July 8, 1992 (for

Model 810 series airplanes). After

replacement, repeat the inspection required

by paragraph (a) of this AD at intervals not

to exceed 1,100 landings or within 14

months, whichever occurs first.

(c) 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.

(d) 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.

(e) The inspections and replacement shall

be done in accordance with Viscount PTL

334, Issue 2, dated July 8, 1992; or Viscount

PTL 205, Issue 2, dated July 8, 1992; as

applicable. 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 Regional Aircraft

Ltd., Engineering Support Manager, Military

Business Unit, Chadderton Works, Greengate,

Middleton, Manchester M24 1SA, England.

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.

(f) This amendment becomes effective on

March 20, 1995.

Issued in Renton, Washington, on February

3, 1995.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–3245 Filed 2–15–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–ANE–11; Amendment 39–

9138; AD 95–03–01]

Airworthiness Directives; General

Electric Company CF6 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to General Electric Company

(GE) CF6–45/–50/–80A series turbofan

engines, that currently requires a onetime ultrasonic and eddy current

inspection of the high pressure

compressor rotor (HPCR) stage 3–9

spool for cracks. This amendment

retains the inspection requirements of

the current AD, but would accelerate the

inspection schedule, and introduce a

repetitive inspection requirement. This

amendment is prompted by a review of

the inspection results to date, which

indicate that the crack occurrence rate is

higher than initially projected. The

actions specified by this AD are

intended to prevent an uncontained

HPCR stage 3–9 spool failure, which

could result in damage to the aircraft.

DATES: Effective March 20, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 20,

1995.

ADDRESSES: The service information

referenced in this AD 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 Federal Aviation Administration

(FAA), New England Region, Office of

the Assistant Chief Counsel, 12 New

England Executive Park, Burlington, MA

01803–5299; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

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: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding airworthiness directive

(AD) 91–20–01, Amendment 39–8035

(56 FR 55230), which is applicable to

General Electric Company (GE) CF6–45/

–50/–80A series turbofan engines, was

published in the Federal Register on

May 3, 1994 (59 FR 22769). That action

proposed to retain the one-time

ultrasonic and eddy current inspection

of the high pressure compressor rotor

(HPCR) stage 3–9 spool for cracks as

required in the current AD, but would

accelerate the inspection schedule, and

introduce a repetitive ultrasonic and

eddy current inspection requirement in

accordance with GE CF6–50 Service

Bulletin (SB) No. 72–1000, Revision 2,

dated September 9, 1993, and GE CF6–

80A SB No. 72–583, Revision 4, dated

September 15, 1993.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Two commenters support the rule as

proposed.

One commenter states that the

repetitive inspection interval of 3,500

cycles in service (CIS) in compliance

paragraph (b) of the proposed rule

should be replaced with 4,000 CIS in