44206 Federal Register / Vol. 62, No. 161 / Wednesday, August 20, 1997 / Rules and Regulations

§39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

97–17–02 Boeing: Amendment 39–10104.

Docket 97–NM–124–AD.

Applicability: Model 777–200 series

airplanes, line numbers 3, 5, 7 through 9

inclusive, 11 through 13 inclusive, 15

through 17 inclusive, and 19 through 22

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 (d) 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 detect and correct loose bushing

retainer nuts of the pivot pins in the

horizontal stabilizer hinge assembly, which

could result in bushing migration and

consequent damage to the adjacent structure,

and reduced controllability of the airplane,

accomplish the following:

(a) Within 150 flight cycles after the

effective date of this AD, torque the bushing

retainer nuts to the new torque value of 1,000

to 1,500 in-lbs, in accordance with Figure 2

of the Boeing Service Bulletin 777–53–0006,

dated May 8, 1997. Repeat the torquing

thereafter at intervals not to exceed 1,000

flight cycles.

Note 2: Where there are differences

between the AD and the service bulletin, the

AD prevails.

(b) If any bushing retainer nut is loose and

is not correctly attached to the bushing, prior

to further flight, perform a visual inspection

to determine whether bushing migration has

occurred, in accordance with Figure 2 of the

Boeing Service Bulletin 777–53–0006, dated

May 8, 1997.

(1) If bushing migration has not occurred,

prior to further flight, tighten the bushing

retainer nuts in accordance with Figure 2 of

the service bulletin. Repeat the visual

inspection thereafter at intervals not to

exceed 1,000 flight cycles.

(2) If bushing migration has occurred, prior

to further flight, inspect/replace the bushing

and other affected components and repair

any damage, in accordance with a method

approved by the Manager, Seattle Aircraft

Certification Office (ACO), FAA, Transport

Airplane Directorate.

(c) Accomplishment of installing an antirotation bracket in accordance with Figure 3

of Boeing Service Bulletin 777–53–0006,

dated May 8, 1997, constitutes terminating

action for the repetitive inspection

requirements of this AD.

(d) 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, Seattle

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Seattle ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(e) 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.

(f) Certain actions shall be done in

accordance with Boeing Service Bulletin

777–53–0006, dated May 8, 1997. 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 Boeing

Commercial Airplane Group, P.O. Box 3707,

Seattle, Washington 98124–2207. 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.

(g) This amendment becomes effective on

September 4, 1997.

Issued in Renton, Washington, on August

11, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–21773 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–167–AD; Amendment

39–10099; AD 97–16–07]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB 2000 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Saab Model SAAB

2000 series airplanes, that requires

replacement of the existing fire, tailpipe,

and bleed-air overheat detector control

units with new, improved units. This

amendment is prompted by reports

indicating that false engine and

auxiliary power unit (APU) fire

warnings were issued from the fire

detector control units due to moisture or

induced voltages of the detector control

unit. The actions specified by this AD

are intended to prevent such false fire

warnings, which could result in

unnecessary diversion of the airplane,

and resultant increased risks to the

airplane, passengers, and crew, and the

potential for an overweight landing.

DATES: Effective September 24, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of September

24, 1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from SAAB Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

Sweden. 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:

Ruth Harder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–1721; fax (425) 227–1149.

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 Saab Model

SAAB 2000 series airplanes was

published in the Federal Register on

May 1, 1997 (62 FR 23695). That action

proposed to require replacement of the

existing fire, tailpipe, and bleed leak

detector control units with new,

improved units.

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.

Revised Service Bulletin Citation

The final rule has been revised to

clarify that Saab Service Bulletin 2000–

26–002, which was cited in the proposal

as the appropriate source of service

information, includes Attachments 1

and 2. These attachments specify

procedures from the Aircraft

Maintenance Manual for removal and

installation of the bleed-air overheat

detection system control unit.

Conclusion

After careful review of the available

data, the FAA has determined that air

safety and the public interest require the
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-