Federal Register / Vol. 60, No. 39 / Tuesday, February 28, 1995 / Rules and Regulations 10805

(j) The actions required by this AD shall be done in accordance with the following alert service bulletin:

Document No. Pages Revision Date

PW ASB No. 5842 .................................................................................. 1–17 3 ............................................................ Oct. 10, 1990.

Appendix A .............................................................................................. 1–2 Original ................................................. May 26, 1989.

Appendix B .............................................................................................. 1–23 3 ............................................................ Oct. 10, 1990.

Appendix C .............................................................................................. 1–7 Original ................................................. May 26, 1989.

Total pages: 49.

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 Pratt & Whitney, 400 Main St., East

Hartford, CT 06108. Copies may be inspected

at the FAA, New England Region, Office of

the Assistant Chief Counsel, 12 New England

Executive Park, Burlington, MA; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(k) This amendment becomes effective on

March 30, 1995.

Issued in Burlington, Massachusetts, on

January 26, 1995.

Michael H. Borfitz,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 95–2693 Filed 2–27–95; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 94–NM–84–AD; Amendment

39–9145; AD 95–03–08]

Airworthiness Directives; Aerospatiale

Model ATR42–300 and –320 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Aerospatiale Model

ATR42–300 and –320 series airplanes,

that requires an inspection to determine

the model and orientation of certain

flight control rods, and replacement

with modified rods, if necessary. This

amendment is prompted by reports of

corrosion found on the pitch trim and

rudder trim rods. The actions specified

by this AD are intended to prevent

problems associated with corrosion of

the flight control rods, which could

compromise the required strength of

these items.

DATES: Effective on March 30, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 30,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from Aerospatiale, 316 Route de

Bayonne, 31060 Toulouse, Cedex 03,

France. 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:

Sam Grober, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–1187; fax (206) 227–1100.

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 Aerospatiale

Model ATR42 series airplanes was

published in the Federal Register on

July 21, 1994 (59 FR 37182). That action

proposed to require an inspection to

determine the orientation of the end of

rudder trim and elevator trim fail-safe

rods, and replacement of those rods

having upwards-oriented ends.

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, Aerospatiale,

requests that the compliance time

specified in proposed paragraph (a)(1)

for replacement of SARMA-type rods be

extended to 18 months. The proposed

rule would require that these rods be

replaced prior to further flight after they

are identified during the proposed

inspection. The commenter considers

this replacement requirement to be too

restrictive. The FAA does not concur.

The rule provides for a compliance time

of 18 months for accomplishing the onetime inspection to determine if these

types of rods are installed on the

airplane. The FAA finds no justification

for providing an additional time

thereafter for replacement of the

discrepant rods. The FAA does not

consider the 18-month compliance time

to be overly restrictive, since it provides

ample time for operators to schedule the

inspection during regularly scheduled

maintenance and to acquire necessary

parts for replacement. However, under

the provisions of paragraph (b) of the

final rule, if an operator were to find

itself in a situation in which

replacement parts were not immediately

available, it could request approval for

the use of an alternative method of

compliance until parts became

available.

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.

The FAA estimates that 128 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 4
10806 Federal Register / Vol. 60, No. 39 / Tuesday, February 28, 1995 / Rules and Regulations

work hours per airplane 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 $30,720, or $240 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.

Should replacement of any of the

flight control rods be necessary, the

number of work hours and the cost of

required parts would vary according to

the type of replacement accomplished.

In a ‘‘worst case scenario’’ (both subject

rods needing replacement), the cost of

parts would be approximately $6,000

per airplane. Labor necessary to

accomplish replacement of a rod(s)

would vary from 54 to 87 work hours,

at an average labor rate of $60 per work

hour.

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:

95–03–08 Aerospatiale: Amendment 39–

9145. Docket 94–NM–84–AD.

Applicability: Model ATR42–300 and -320

series airplanes on which Aerospatiale

Modification 02723 has not been installed,

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 problems associated with

corrosion of the flight control rods, which

could compromise the required strength of

these items, accomplish the following:

(a) Within 18 months after the effective

date of this AD, visually inspect the elevator

trim and rudder trim fail-safe rods to

determine the model and the orientation of

the open end of the rod, in accordance with

Aerospatiale Service Bulletin ATR42–27–

0071, dated February 23, 1994.

(1) If a SARMA-type rod is installed at

either of these locations, prior to further

flight, replace that rod with a modified rod,

in accordance with Aerospatiale Service

Bulletin ATR42–27–0049, Revision 2, dated

May 16, 1991.

(2) If a TAC-type rod is installed at either

of these locations, and if the open end of the

rod is oriented in any direction other than

downwards, prior to further flight,

accomplish the reverse installation

procedures specified in Aerospatiale Service

Bulletin ATR42–27–0048, Revision 2, dated

May 16, 1991.

(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 §§ 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 actions shall be done in accordance

with the following Aerospatiale Service

Bulletins, which contain the specified

effective pages:

Service bulletin number and date Page No.

Revision

level shown

on page

Date shown on

page

ATR42–27–0071, Feb. 23, 1994 ................................................................................. 1–8 ............................... Original ........ Feb. 23, 1994.

ATR42–27–0048 ..........................................................................................................

Revision 2 ....................................................................................................................

May 16, 1991 ...............................................................................................................

1, 2, 4–6 .......................

3, 8, 9 ...........................

7 ...................................

2 ..................

Original ........

1 ..................

May 16, 1991.

June 22, 1990.

Nov. 21, 1990.

ATR42–27–0049 ..........................................................................................................

Revision 2 ....................................................................................................................

May 16, 1991 ...............................................................................................................

1, 2, 4 ...........................

3, 5, 6, 8, 11 .................

7, 9, 10 .........................

2 ..................

Original ........

1 ..................

May 16, 1991.

Sept. 14, 1990.

Nov. 21, 1990.

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 Aerospatiale, 316 Route de Bayonne,

31060 Toulouse, Cedex 03, France. 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.
Federal Register / Vol. 60, No. 39 / Tuesday, February 28, 1995 / Rules and Regulations 10807

(e) This amendment becomes effective on

March 30, 1995.

Issued in Renton, Washington, on February

6, 1995.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–3355 Filed 2–27–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–83–AD; Amendment

39–9144; AD 95–03–07]

Airworthiness Directives; Aerospatiale

Model ATR72–101, –102, –201, and

–202 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Aerospatiale Model

ATR72 series airplanes, that requires an

inspection to determine the model and

orientation of certain flight control rods,

and replacement of the rods with

modified rods, if necessary. This

amendment is prompted by reports of

corrosion found on the pitch and rudder

trim and rudder travel limiter fail-safe

rods. The actions specified by this AD

are intended to prevent problems

associated with corrosion of the flight

control rods, which could compromise

the required strength of these items.

DATES: Effective March 30, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 30,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from Aerospatiale, 316 Route de

Bayonne, 31060 Toulouse, Cedex 03,

France. 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:

Sam Grober, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–1187; 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 Aerospatiale

Model ATR72 series airplanes was

published in the Federal Register on

July 27, 1994 (59 FR 38139). That action

proposed to require an inspection to

determine the model and orientation of

certain flight control rods, and

replacement of the rods with modified

rods, if necessary.

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.

The FAA has determined that air safety

and the public interest require the

adoption of the rule as proposed.

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 effects 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.

Additionally, 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.

The FAA estimates that 28 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 6

work hours per airplane to accomplish

the required inspection, 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 $10,080, or $360 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.

Should replacement of any of the

flight control rods be necessary, the

number of work hours and the cost of

required parts will vary according to the

type of replacement accomplished. In a

‘‘worst case scenario’’ (all subject rods

needing replacement), the cost of parts

will be approximately $8,200 per

airplane. Labor necessary to accomplish

replacement of a rod(s) will vary from

2 work hours to 10 work hours, at an

average labor rate of $60 per work hour.

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.