Federal Register / Vol. 62, No. 161 / Wednesday, August 20, 1997 / Rules and Regulations 44207

adoption of the rule with the change

previously described. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

Cost Impact

The FAA estimates that 2 Saab Model

SAAB 2000 series airplanes of U.S.

registry will be affected by this AD, that

it will take approximately 3 work hours

per airplane to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will be provided by the manufacturer at

no cost to the operators. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be $360,

or $180 per airplane.

The 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.

Regulatory Impact

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. 106(g), 40113, 44701.

§39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

97–16–07 Saab Aircraft AB: Amendment

39–10099. Docket 96–NM–167–AD.

Applicability: Model SAAB 2000 series

airplanes having serial numbers 005 through

029 inclusive, certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 request approval for an

alternative method of compliance in

accordance with paragraph (c) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent false fire warning inputs of the

engines and auxiliary power unit (APU),

which could result in unnecessary diversion

of the airplane, resultant increased risks to

the airplane, passengers, and crew, and the

potential for an overweight landing;

ccomplish the following:

(a) Within 4 months after the effective date

of this AD, replace the existing fire (engine/

APU), tailpipe, and bleed-air overheat

detector control units with new, improved

control units, in accordance with Saab

Service Bulletin 2000–26–002, dated May 9,

1995, including Attachments 1 and 2.

(b) As of the effective date of this AD, no

person shall install a fire, tailpipe, or bleedair detector control unit having part number

25000020–21, 25000021–31, or 25000020–11

on any airplane.

(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 replacement shall be done in

accordance with Saab Service Bulletin 2000–

26–002, dated May 9, 1995, including

Attachments 1 and 2, which includes the

following list of effective pages:

Page No.

Revision

level shown

on page

Date shown

on page

1–6 ............... Original ........ May 9, 1995.

Attachment 1

1–3 ............... Original ........ Not Dated.

Attachment 2

1–3 ............... Original ........ Not Dated.

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 SAAB Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

Sweden. 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

September 24, 1997.

Issued in Renton, Washington, on July 29,

1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–21791 Filed 8–19–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–SW–27–AD; Amendment

39–10108; AD 97–17–06]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron, Inc. Model 214ST

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Bell Helicopter Textron,

Inc. (BHTI) Model 214ST helicopters,

that requires replacement of each

emergency float inflation solenoid valve

(valve). This amendment is prompted by

two inadvertent inflations of emergency

float systems that resulted from self-
44208 Federal Register / Vol. 62, No. 161 / Wednesday, August 20, 1997 / Rules and Regulations

activations of the valves. The actions

specified by this AD are intended to

prevent self-activation of the valves, and

subsequent inadvertent inflation of the

emergency float system, which could

lead to loss of control of the helicopter.

EFFECTIVE DATE: September 24, 1997.

FOR FURTHER INFORMATION CONTACT: Mr.

Uday Garadi, Aerospace Engineer, FAA,

Rotorcraft Certification Office, 2601

Meacham Blvd., Fort Worth, Texas

76137, telephone (817) 222–5157; fax

(817) 222–5960.

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 Model 214ST

helicopters, equipped with an

emergency float kit, part number (P/N)

214–706–120, containing valves, P/N

214–073–929–103 or –105, in solenoid

valve assemblies (valve assemblies), P/

N 214–073–940–101 or –103, was

published in the Federal Register on

November 20, 1996 (61 FR 59033). That

action proposed to require replacement

of all existing valves, P/N 214–073–929–

103 and –105, in valve assemblies, P/N

214–073–940–101 and –103.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on 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.

The FAA estimates that 9 helicopters

of U.S. registry will be affected by this

AD, that it will take approximately 2

work hours per helicopter to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Required parts will cost approximately

$2,100 per helicopter. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$19,980.

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, 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. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive to

read as follows:

AD 97–17–06 Bell Helicopter Textron, Inc.:

Amendment 39–10108. Docket No. 96–

SW–27–AD.

Applicability: Model 214ST helicopters,

equipped with an emergency float kit, part

number (P/N) 214–706–120, containing

emergency float inflation solenoid valves,

P/N 214–073–929–103 or –105, in solenoid

valve assemblies, P/N 214–073–940–101 or

–103, certificated in any category.

Note 1: This AD applies to each helicopter

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

helicopters 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 helicopter

from the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent self-activation of the valves,

and subsequent inadvertent inflation of the

emergency float system, which could lead to

loss of control of the helicopter, accomplish

the following:

(a) At the next scheduled ‘‘B’’ (250 hour)

inspection, or 180-day float inspection, or 3-

year float system operational inspection,

whichever occurs first, remove solenoid

valves, P/N 214–073–929–103 or –105, from

solenoid valve assemblies, P/N 214–073–

940–101 or –103, and replace with solenoid

valves, P/N 214–073–929–107.

Note 2: Solenoid valve assemblies, P/N

214–073–940, consist of a valve, P/N 214–

073–929 and a decal, P/N 31–023–8B.

Solenoid valve assembly, P/N 214–073–940–

105, contains solenoid valve, P/N 214–073–

929–107.

(b) Installation of solenoid valves, P/N

214–073–929–107, or solenoid valve

assemblies, P/N 214–073–940–105,

constitutes terminating action for the

requirements of this AD.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Certification

Office.

(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, Rotorcraft

Certification Office, Rotorcraft Directorate,

FAA. Operators shall submit their requests

through an FAA Principal Maintenance

Inspector, who may concur or comment and

then send it to the Manager, Rotorcraft

Certification Office.

(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 helicopter

to a location where the requirements of this

AD can be accomplished.

(e) This amendment becomes effective on

September 24, 1997.

Issued in Fort Worth, Texas, on August 13,

1997.

Larry M. Kelly,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–22044 Filed 8–19–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–53–AD; Amendment

39–10110; AD 96–23–07 R1]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–9–80 Series

Airplanes and Model MD–88 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment revises an

existing airworthiness directive (AD),

applicable to certain McDonnell