Federal Register / Vol. 62, No. 29 / Wednesday, February 12, 1997 / Rules and Regulations 6457

a new airworthiness directive (AD),

amendment 39–9924, to read as follows:

97–03–19 BOEING: Amendment 39–9924.

Docket 95–NM–226–AD. Supersedes AD

92–16–17, Amendment 39–8327.

Applicability: Model 747–100, –200, and

–300 series airplanes equipped with an offwing, two-piece escape slide on Door 3;

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 (e) 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 failure of the escape slide to

deploy, which could delay and possibly

jeopardize the successful emergency

evacuation of an airplane, accomplish the

following:

(a) Within 18 months after November 25,

1992 (the effective date of AD92–16–17,

amendment 39–8327), perform an inspection

of the door opening thrusters of the escape

system in accordance with OEA Service

Bulletin 2174200–25–013, dated July 29,

1991. Repeat this inspection thereafter at

intervals not to exceed 20 months until the

replacement required by paragraph (c) of this

AD is accomplished.

Note 2: Inspections accomplished in

accordance with OEA Service Bulletin

2174200–25–013, Revision 1, dated

September 14, 1993; Revision 2, dated

November 1, 1993; or Revision 3, dated

January 13, 1994; are considered acceptable

for compliance with the inspections specified

in paragraph (a) of this AD.

(b) Within 18 months after November 25,

1992, inspect and modify the door latching

mechanism of the escape slide compartment

in accordance with Boeing Service Bulletin

747–25–2951, dated August 15, 1991.

Note 3: Inspections and modifications

accomplished in accordance with Boeing

Service Bulletin 747–25–2951, Revision 1,

dated May 13, 1993; or Revision 2, dated

September 30, 1993; are considered

acceptable for compliance with the

applicable action specified in paragraph (b)

of this AD.

(c) Within 2 years after the effective date

of this AD, replace the door opening thrusters

having part number (P/N) 60B50077–14 or

–17 with new thrusters having P/N

60B50077–19 in accordance with Boeing

Service Bulletin 747–25–3073, dated

September 21, 1995. Accomplishment of this

replacement terminates the repetitive

inspections required by this AD.

(d) As of 2 years after the effective date of

this AD, only door opening thrusters having

P/N 60B50077–19 shall be installed on any

airplane.

(e) 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

Aircraft Certification Office (ACO), 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, Seattle ACO.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(f) 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.

(g) The inspections and modification shall

be done in accordance with OEA Service

Bulletin 2174200–25–013, dated July 29,

1991; and Boeing Service Bulletin 747–25–

2951, dated August 15, 1991. The

incorporation by reference of those

documents was approved previously by the

Director of the Federal Register, in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51, as of November 25, 1992 (57 FR

47987, October 21, 1992). The replacement

shall be done in accordance with Boeing

Service Bulletin 747–25–3073, dated

September 21, 1995. The incorporation by

reference of that document 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; and OEA

Aerospace Inc., P.O. Box KK, Hwy. 12,

Explosive Technology Road, Fairfield,

California 94533–0659. 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.

(h) This amendment becomes effective on

March 19, 1997.

Issued in Renton, Washington, on January

31, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–3027 Filed 2–11–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–69–AD; Amendment

39–9923; AD 97–03–18]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB SF340A, SAAB 340B, and 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

SF340A, SAAB 340B, and SAAB 2000

series airplanes, that requires

replacement of the hubcap drive

coupling of the main wheel with an

improved coupling. This amendment is

prompted by reports of unexpected

decreases in the pressure of the main

wheel brake due to incorrect

engagement between the main wheel

coupling and the wheel speed

transducer, which can result in false

signals being sent to the anti-skid

control box. The actions specified by

this AD are intended to prevent loss of

brake effectiveness due to a decrease in

the pressure of the main wheel brake.

DATES: Effective March 19, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 19,

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 FAA, Transport

Airplane Directorate, Los Angeles

Aircraft Certification Office, 3960

Paramount Boulevard, Lakewood,

California; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Walter Eierman, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130L, FAA, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California 90712;

telephone (310) 627–5336; fax (310)

627–5210.

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 SF340A, SAAB 340B, and SAAB

2000 series airplanes was published in

the Federal Register on September 4,

1996 (61 FR 46572). That action

proposed to require replacement of the

hubcap drive coupling of the main

wheel with an improved coupling.

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.
6458 Federal Register / Vol. 62, No. 29 / Wednesday, February 12, 1997 / Rules and Regulations

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 235 Model

SAAB SF340A and SAAB 340B series

airplanes and 3 Model SAAB 2000

series airplanes of U.S. registry will be

affected by this AD.

For Model SAAB SF340A and SAAB

340B series airplanes, it will take

approximately 2 work hours per

airplane to accomplish the required

actions, at an average labor rate of $60

per work hour. Required parts will cost

approximately $200 per airplane. Based

on these figures, the cost impact of the

AD on U.S. operators of Model SAAB

340A and SAAB 340B series airplanes is

estimated to be $75,200, or $320 per

airplane.

For Model SAAB 2000 series

airplanes, it will take approximately 2

work hours per airplane to accomplish

the required actions, at an average labor

rate of $60 per work hour. Required

parts will cost approximately $120 per

airplane. Based on these figures, the cost

impact of the proposed AD on U.S.

operators of Model SAAB 2000 series

airplanes is estimated to be $720, or

$240 per airplane.

The cost impact figures discussed

above are 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:

97–03–18 SAAB AIRCRAFT AB:

Amendment 39–9923. Docket 96–NM–

69–AD.

Applicability: Model SAAB SF340A series

airplanes having serial numbers 004 through

159 inclusive; Model SAAB 340B series

airplanes having serial numbers 160 through

378 inclusive; and Model SAAB 2000 series

airplanes having serial numbers 002 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 loss of brake effectiveness due

to a decrease in pressure of the main wheel

brake, accomplish the following:

(a) Within 90 days after the effective date

of this AD, replace each main wheel hubcap

drive coupling having part number (P/N) 40–

91115 with a main wheel hubcap drive

coupling having P/N 40–91115, Rev. D, in

accordance with Saab Service Bulletin SAAB

340–32–107, dated January 18, 1996 (for

Model SAAB SF340A and SAAB 340B series

airplanes), or Saab Service Bulletin SAAB

2000–32–019, dated January 18, 1996 (for

Model SAAB 2000 series airplanes), as

applicable.

Note 2: The Saab service bulletins

reference Crane Hydro-Aire Division Service

Bulletins 140–041–32–1 (for wheel hubcaps

having part number 140–04120) and 140–

159–32–1 (for wheel hubcaps having part

number 140–15920), both dated December

21, 1995, as additional sources of service

information for replacement of the hubcap

drive coupling.

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

person shall install on any airplane a main

wheel hubcap drive coupling having P/N 40–

91115 in a wheel hubcap having P/N 140–

04120 (for Model SAAB SF340A and SAAB

340B series airplanes), or P/N 140–15920 (for

Model SAAB 2000 series airplanes), as

applicable.

(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, Los

Angeles Aircraft Certification Office (ACO),

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, Los Angeles ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(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 SAAB

340–32–107, dated January 18, 1996, or Saab

Service Bulletin SAAB 2000–32–019, dated

January 18, 1996, 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 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 FAA, Transport

Airplane Directorate, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment becomes effective on

March 19, 1997.

Issued in Renton, Washington, on January

31, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–3026 Filed 2–11–97; 8:45 am]

BILLING CODE 4910–13–U