37478 Federal Register / Vol. 65, No. 116 / Thursday, June 15, 2000 / Rules and Regulations

servo-control, in accordance with the

applicable service bulletin.

Note 2: Accomplishment of an inspection

in accordance with Airbus Service Bulletin

A330–27–3062 (for Model A330 series

airplanes) or A340–27–4072 (for Model A340

series airplanes), both dated February 5,

1999; is considered acceptable for

compliance with the initial inspection

requirements of paragraph (a) of this AD.

Note 3: The Airbus service bulletins

reference SAMM Service Bulletin SC4800–

27–34–06, dated January 2, 1999, as an

additional source of service information for

accomplishment of the dye penetrant

inspection specified by paragraph (a)(2) of

this AD.

Alternative Methods of Compliance

(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,

International Branch, ANM–116, 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, International Branch,

ANM–116.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(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.

Incorporation by Reference

(d) The actions shall be done in accordance

with Airbus Service Bulletin A330–27–3062,

Revision 01, dated July 21, 1999; or Airbus

Service Bulletin A340–27–4072, Revision 01,

dated July 21, 1999; 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 Airbus

Industrie, 1 Rond Point Maurice Bellonte,

31707 Blagnac Cedex, 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.

Note 5: The subject of this AD is addressed

in French airworthiness directives 2000–

025–109(B) R1 and 2000–024–135(B) R1,

both dated March 8, 2000.

(e) This amendment becomes effective on

July 20, 2000.

Issued in Renton, Washington, on June 7,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14882 Filed 6–14–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–51–AD; Amendment

39–11785; AD 2000–12–07]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB SF340A and SAAB 340B 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 and SAAB 340B series

airplanes, that requires a one-time

inspection to detect corrosion and

scratches on the bearing housing

surfaces of the support assembly on the

main landing gear (MLG), and corrective

actions, if necessary. This amendment is

prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified by this AD are

intended to prevent corrosion in the

inboard and outboard bearing housings

of the MLG support assembly, which

could result in fatigue cracks in the

support assembly and lead to failure of

the MLG.

DATES: Effective July 20, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 20,

2000.

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:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

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 SF340A and SAAB 340B series

airplanes was published in the Federal

Register on January 5, 2000 (65 FR 395).

That action proposed to require a onetime inspection to detect corrosion and

scratches on the bearing housing

surfaces of the support assembly on the

main landing gear, and corrective

actions, if necessary.

Consideration of Comments Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the two

comments received.

Request To Include Optional Repair

Procedure to This AD

One commenter, an operator, requests

that the optional repair procedure,

included in a note in step 2.C.(1)(b)10

of the Accomplishment Instructions of

Saab Service Bulletin 340–57–036,

dated October 20, 1999, be added to the

proposed AD. That procedure specifies

certain options for follow-on repair

based on the depth and extent of

damage after rework. One option would

require repair of the main landing gear

(MLG) support assembly within 4,000

flight cycles after the inspection.

Another option would require

reinstalling the bearings for the MLG

assembly and continuing to operate the

airplane an additional 4,000 flight

cycles before the final repair is

accomplished. The commenter adds that

[without having these options] ‘‘we

foresee a serious maintenancescheduling issue’’ due to the large

number of Saab Model SAAB 340 series

airplanes in its fleet (presently 115).

The FAA concurs with the

commenter’s request to include in this

AD the two options specified in the

service bulletin. Although those options

were inadvertently omitted in the

proposed AD, both options are included

in this AD. The FAA has determined

that, for damage within certain limits

after rework, deferral of the final repair

of the MLG support assembly for 4,000

flight cycles will adequately address the

identified unsafe condition and is

acceptable for the requirements of this

AD.

Request To Revise Cost Estimate

One commenter states that ‘‘unless

there is a policy to address inspections

only and not include preparation,

corrective action, and close up costs, the

costs are underestimated in the NPRM.’’

The service bulletin includes detailed

costs for the actions specified, which

include access, inspection, corrective

actions, close up, and test. The

commenter adds that, if operators

Federal Register / Vol. 65, No. 116 / Thursday, June 15, 2000 / Rules and Regulations 37479

accomplish those actions when the

MLG’s are removed for overhaul or

repair, no extra costs are necessary for

the removal/reinstallation of shock

struts and drag braces. However, if such

actions are not accomplished during

overhaul or repair of the MLG’s,

removal/installation will require an

additional 8 hours. In addition, the costs

will vary according to the damage

found.

The FAA does not concur with the

commenter’s request to revise the cost

impact information presented in the

proposed AD, which describes only the

‘‘direct’’ costs of the specific actions

required by this AD. The number of

work hours necessary to accomplish the

required actions, specified as 2 work

hours in the cost impact information,

below, was provided to the FAA by the

manufacturer based on the best data

available to date. That number

represents the time necessary to perform

only the actions actually required by

this AD. The FAA recognizes that, in

accomplishing the requirements of any

AD, operators may incur ‘‘incidental’’

costs in addition to the ‘‘direct’’ costs.

However, the cost analysis in AD

rulemaking actions typically does not

include incidental costs, such as the

time required to gain access and close

up, planning time, or time necessitated

by other administrative actions. The

FAA points out that because incidental

costs may vary significantly from

operator to operator, they are almost

impossible to calculate. For these

reasons, no change to the final rule is

necessary in this regard.

Explanation of Changes Made to This

Final Rule

The FAA has made the following

changes:

• Revised paragraph (b) and added

paragraphs (b)(1) and (b)(2) in the final

rule.

• Added a reference to ‘‘paragraph

(b)’’ in paragraph (c) of the final rule.

Conclusion

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

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

The FAA estimates that 291 Model

SAAB SF340A and SAAB 340B series

airplanes of U.S. registry will be affected

by this AD, that it will take

approximately 2 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 cost impact of the AD on

U.S. operators is estimated to be

$34,920, or $120 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 a substantial direct effect 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, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

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:

2000–12–07 SAAB Aircraft AB:

Amendment 39–11785. Docket 99–NM–

51–AD.

Applicability: Model SAAB SF340A, serial

numbers –004 through –159 inclusive; and

SAAB 340B series airplanes, serial numbers

–160 through –444 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

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 prevent corrosion in the inboard and

outboard bearing housings of the support

assembly of the main landing gear (MLG),

which could result in fatigue cracks in the

support assembly and lead to failure of the

MLG, accomplish the following:

Initial Inspection

(a) At the applicable time specified in

paragraph (a)(1), (a)(2), (a)(3), or (a)(4) of this

AD: Perform a one-time general visual

inspection of the eight bearing housing

surfaces of the MLG to detect corrosion or

scratches, in accordance with Saab Service

Bulletin 340–57–036, dated October 20, 1999.

(1) For airplanes with 32,000 or more total

flight cycles as of the effective date of this

AD, the inspection is to be performed within

4,000 flight cycles after the effective date of

this AD.

(2) For airplanes with 24,000 or more and

fewer than 32,000 total flight cycles as of the

effective date of this AD, the inspection is to

be performed within 6,000 flight cycles after

the effective date of this AD.

(3) For airplanes with 12,000 or more and

fewer than 24,000 total flight cycles as of the

effective date of this AD, the inspection is to

be performed prior to the accumulation of

24,000 total flight cycles, or within 6,000

flight cycles after the effective date of this

AD, whichever occurs later.

(4) For airplanes with fewer than 12,000

total flight cycles as of the effective date of

this AD, the inspection is to be performed

prior to the accumulation of 12,000 total

flight cycles, or within 6,000 flight cycles

after the effective date of this AD, whichever

occurs later.

Note 2: For the purposes of this AD, a

general visual inspection is defined as: ‘‘A

visual examination of an interior or exterior

area, installation, or assembly to detect

obvious damage, failure, or irregularity. This

level of inspection is made under normally

available lighting conditions such as

daylight, hangar lighting, flashlight, or droplight, and may require removal or opening of

access panels or doors. Stands, ladders, or

37480 Federal Register / Vol. 65, No. 116 / Thursday, June 15, 2000 / Rules and Regulations

platforms may be required to gain proximity

to the area being checked.’’

Corrective Actions

(b) Except as provided by paragraph (c) of

this AD: If, during the inspection required by

paragraph (a) of this AD, any corrosion or

scratch is detected that is within the limits

specified in Saab Service Bulletin 340–57–

036, dated October 20, 1999, prior to further

flight, perform corrective actions (including

rework, an eddy current inspection, and

repair) in accordance with Steps 2.B. and 2.C.

of the Accomplishment Instructions of the

service bulletin.

(1) If, after rework, the depth of the damage

is less than or equal to 0.15 mm (0.006

inches) AND the damage does not exceed 15

percent of the area, no further action is

required by this AD.

(2) If, after rework, the depth of the damage

exceeds 0.15 mm (0.006 inches) but is less

than or equal to 1.1 mm (0.043 inches), AND

the damage does not exceed 30 percent of the

area: Within 4,000 flight cycles after

accomplishment of the inspection required

by paragraph (a), repair the MLG support

assembly in accordance with the service

bulletin. Following the repair, no further

action is required by this AD.

(c) If, during any inspection required by

this AD, a discrepancy is detected for which

the service bulletin specifies to contact Saab

for appropriate action [including any crack or

any corrosion or scratch that exceeds 1.1 mm

(0.043 in) after applicable rework has been

performed as required by paragraph (b) of

this AD]: Prior to further flight, repair in

accordance with a method approved by the

Manager, International Branch, ANM–116,

Transport Airplane Directorate; or the

Luftfartsverket (LFV) (or its delegated agent).

For a repair method to be approved by the

Manager, International Branch, ANM–116, as

required by this paragraph, the Manager’s

approval letter must specifically reference

this AD.

Alternative Methods of Compliance

(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,

International Branch, ANM–116, 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, International Branch,

ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(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.

Incorporation by Reference

(f) Except as specified by paragraph (c) of

this AD, the inspections and corrective

actions shall be done in accordance with

Saab Service Bulletin 340–57–036, dated

October 20, 1999. 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.

Note 4: The subject of this AD is addressed

in Swedish airworthiness directive 1–146,

dated October 20, 1999.

(g) This amendment becomes effective on

July 20, 2000.

Issued in Renton, Washington, on June 7,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14951 Filed 6–14–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–56–AD; Amendment

39–11793; AD 2000–12–15]

RIN 2120–AA64

Airworthiness Directives; Dassault

Model Falcon 2000, Mystere-Falcon

900, Falcon 900EX, Fan Jet Falcon,

Mystere-Falcon 50, Mystere-Falcon 20,

Mystere-Falcon 200, and Falcon 10

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Dassault Model Falcon

2000, Mystere-Falcon 900, Falcon

900EX, Fan Jet Falcon, Mystere-Falcon

50, Mystere-Falcon 20, Mystere-Falcon

200, and Falcon 10 series airplanes, that

requires repetitive tests and inspections

to detect discrepancies of the overwing

emergency exit; and corrective action, if

necessary. This amendment is prompted

by issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by this AD are

intended to prevent failure of the

overwing emergency exits to open, and

consequent injury to passengers or crew

members during an emergency

evacuation.

EFFECTIVE DATE: July 20, 2000.

ADDRESSES: Information pertaining to

this amendment may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

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 all Dassault Model

Falcon 2000, Mystere-Falcon 900,

Falcon 900EX, Fan Jet Falcon, MystereFalcon 50, Mystere-Falcon 20, MystereFalcon 200, and Falcon 10 series

airplanes was published in the Federal

Register on April 24, 2000 (65 FR

21679). That action proposed to require

repetitive tests and inspections to detect

discrepancies of the overwing

emergency exit; and corrective action, if

necessary.

Comments

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.

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 767 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 1

work hour per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $46,020, or $60 per airplane, per

inspection cycle.

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 a substantial direct effect on

the States, on the relationship between

the national Government and the States,

or on the distribution of power and

responsibilities among the various