Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations 34581

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:

98–13–33 Airbus Industrie: Amendment

39–10624. Docket 97–NM–257–AD.

Applicability: All Model A300, A300–600,

and A310 series airplanes, 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 detect and correct desynchronization of

the rudder servo actuators, which could

result in reduced structural integrity of the

rudder attachments and reduced

controllability of the airplane, accomplish

the following:

(a) Prior to accumulation of 1,300 total

flight hours, or within 500 flight hours after

the effective date of this AD, whichever

occurs later, and thereafter at intervals not to

exceed 1,300 flight hours: Perform a test to

detect desynchronization of the rudder servo

actuators in accordance with Airbus Service

Bulletin A300–27–0188, Revision 2, dated

October 1, 1997 (for Model A300 series

airplanes); A300–27–6036, Revision 2, dated

October 1, 1997 (for Model A300–600 series

airplanes); or A310–27–2082, Revision 2,

dated October 1, 1997 (for Model A310 series

airplanes); as applicable. If any

desynchronization (rudder movement) is

detected, prior to further flight, either adjust

or replace, as applicable, the spring rod of the

affected rudder servo actuator in accordance

with the applicable service bulletin.

Note 2: A test to detect desynchronization

of the rudder servo actuators, if

accomplished prior to the effective date of

this AD in accordance with Airbus Service

Bulletin A300–27–0188, dated October 24,

1996, or Revision 1, dated November 5, 1996

(for Model A300 series airplanes); A300–27–

6036, dated October 24, 1996, or Revision 1,

dated November 5, 1996 (for Model A300–

600 series airplanes); or A310–27–2082,

dated October 24, 1996, or Revision 1, dated

November 5, 1996 (for Model A310 series

airplanes); is considered acceptable for

compliance with the initial test required by

paragraph (a) of this AD.

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

this AD, if any desynchronization (rudder

movement) greater than the limit specified in

Paragraph B of the Accomplishment

Instructions of the applicable service bulletin

is detected during any test required by

paragraph (a), prior to further flight,

accomplish either paragraph (b)(1) or (b)(2) of

this AD, in accordance with Airbus Service

Bulletin A300–55–0044, dated October 22,

1996 (for Model A300 series airplanes);

A300–55–6023, dated October 22, 1996 (for

Model A300–600 series airplanes); or A310–

55–2026, dated October 22, 1996 (for Model

A310 series airplanes); as applicable.

(1) Conduct a visual inspection, high

frequency eddy current inspection, or

ultrasonic inspection, as applicable, to detect

cracking of the rudder attachments; and

repeat the inspection thereafter, as

applicable, at the intervals specified in the

applicable service bulletin. Or

(2) Modify the rudder attachments to cold

expand the rivet holes.

(c) If any crack is found during any

inspection or modification required by

paragraph (b) of this AD, and the applicable

service bulletin specifies to contact Airbus

for an appropriate action: Prior to further

flight, repair the affected structure in

accordance with a method approved by the

Manager, International Branch, ANM–116,

FAA, Transport Airplane Directorate, or in

accordance with a method approved by the

Direction Generale de l’Aviation Civile

(DGAC), which is the airworthiness authority

for France.

(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. 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.

(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) Except as provided in paragraph (c) of

this AD, the repetitive inspections and repair

shall be done in accordance with Airbus

Service Bulletin A300–55–0044, dated

October 22, 1996; Airbus Service Bulletin

A300–55–6023, dated October 22, 1996; or

Airbus Service Bulletin A310–55–2026,

dated October 22, 1996, as applicable.

Testing for desynchronization shall be done

in accordance with Airbus Service Bulletin

A300–27–0188, Revision 2, dated October 1,

1997; Airbus Service Bulletin A300–27–6036,

Revision 2, dated October 1, 1997; or Airbus

Service Bulletin A310–27–2082, Revision 2,

dated October 1, 1997, 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 4: The subject of this AD is addressed

in French airworthiness directive 96–242–

208(B) R2, dated November 19, 1997.

(g) This amendment becomes effective on

July 30, 1998.

Issued in Renton, Washington, on June 16,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–16491 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–329–AD; Amendment

39–10623; AD 98–13–32]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F.28 Mark 0100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Fokker Model F.28

Mark 0100 series airplanes, that requires

interim inspections to detect

discrepancies of the main fitting

subassembly of the main landing gear,

and follow-on corrective actions, if

necessary. This amendment also

requires a one-time inspection to detect

discrepancies of the fitting, repair of the

fitting, if necessary, and application of

new surface protection on the fitting,

which would terminate the interim

inspections. 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 cracking of the

main fitting subassembly of the main

landing gear, which could result in

collapse of the main landing gear.
34582 Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations

DATES: Effective July 30, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 30,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Fokker Services B.V., Technical

Support Department, P.O. Box 75047,

1117 ZN Schiphol Airport, the

Netherlands; or from Messier-Dowty

Ltd., Cage: K0654, Cheltenham Road,

Gloucester, GL2 9QH, England. 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 Fokker

Model F.28 Mark 0100 series airplanes

was published in the Federal Register

on April 2, 1998 (63 FR 16165). That

action proposed to require interim

inspections to detect discrepancies of

the main fitting subassembly of the

main landing gear, and follow-on

corrective actions, if necessary. That

action also proposed to require a onetime inspection to detect discrepancies

of the fitting, repair of the fitting, if

necessary, and application of new

surface protection on the fitting.

Accomplishment of these actions would

terminate the interim inspections.

Comments

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.

Request to Cite Earlier Revision of

Service Information

One commenter requests that

provisions be added to allow

accomplishment of inspection and

rework required by paragraph (b) of the

proposed AD in accordance with

Revision 1 of Messier-Dowty Service

Bulletin F100–32–86 in addition to

Revision 2, as proposed in the NPRM.

The FAA concurs. Since Revision 2 of

the service bulletin contains no

substantive differences from Revision 1,

the FAA has determined that the actions

required by paragraph (b) of this AD

may be accomplished in accordance

with Messier-Dowty Service Bulletin

F100–32–86, including Appendix A and

Appendix B; all Revision 1, all dated

November 1, 1996. A ‘‘NOTE’’ has been

added to the final rule to give credit to

operators who may have previously

accomplished the required actions in

accordance with the earlier revision of

the service bulletin.

Explanation of Changes Made to

Proposal

In the proposal, the FAA

inadvertently omitted references to

Appendices A and B, both Revision 1,

both dated November 1, 1996, of

Messier-Dowty Service Bulletin F100–

32–86, Revision 2, dated July 3, 1997.

Therefore, the FAA has revised the final

rule accordingly.

Conclusion

After careful review of the available

data, including the comment 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.

Cost Impact

The FAA estimates that 127 airplanes

of U.S. registry will be affected by this

AD.

It will take approximately 2 work

hours per airplane to accomplish the

required interim inspections. Based on

an average labor rate of $60 per work

hour, the cost impact of the required

interim inspections on U.S. operators is

estimated to be $15,240, or $120 per

airplane, per inspection cycle.

It will take approximately 14 work

hours per airplane to accomplish the

required terminating actions. Based on

an average labor rate of $60 per work

hour the cost impact of the required

terminating actions on U.S. operators is

estimated to be $106,680, or $840 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:

98–13–32 Fokker: Amendment 39–10623.

Docket 97–NM–329–AD.

Applicability: Model F.28 Mark 0100 series

airplanes, equipped with Messier-Dowty

main landing gear units having the part

numbers and serial numbers specified in

Messier-Dowty Service Bulletin F100–32–86,

Revision 2, dated July 3, 1997, including

Appendix A, Revision 1, dated November 1,

1996, and Appendix B, Revision 1, dated

November 1, 1996; 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
Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations 34583

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 cracking of the main fitting

subassembly of the main landing gear, which

could result in collapse of the main landing

gear, accomplish the following:

(a) Within 60 days after the effective date

of this AD, perform a visual and an eddy

current inspection to detect discrepancies

(paint damage, corrosion or cracking) of the

main fitting subassembly of the main landing

gear, in accordance with Appendix B,

Revision 1, dated November 1, 1996, of

Messier-Dowty Service Bulletin F100–32–86,

Revision 2, dated July 3, 1997.

(1) If no discrepancy is detected, or if any

discrepancy is detected that is within the

limits specified in Appendix B of the service

bulletin: Repeat the inspections required by

paragraph (a) of this AD thereafter at

intervals not to exceed 60 days.

(2) If any discrepancy is detected that is

outside the limits specified in Appendix B of

the service bulletin: Prior to further flight,

accomplish the requirements of paragraph (b)

of this AD.

(b) Within 6 months after the effective date

of this AD, perform a one-time eddy current

inspection and a one-time visual inspection

to detect discrepancies (paint damage,

corrosion, or cracking) of the main fitting

subassembly of the main landing gear, in

accordance with the Accomplishment

Instructions of Messier-Dowty Service

Bulletin F100–32–86, Revision 2, dated July

3, 1997, including Appendix A, Revision 1,

dated November 1, 1996, and Appendix B,

Revision 1, dated November 1, 1996.

Accomplishment of the actions required by

this paragraph constitutes terminating action

for the requirements of this AD.

(1) If no discrepancy is detected, prior to

further flight, apply a protective treatment to

the main fittings in accordance with the

service bulletin.

(2) If any discrepancy is detected that can

be repaired within the limits specified in the

service bulletin, prior to further flight, repair

the discrepancy, and apply a protective

treatment to the main fittings, in accordance

with the service bulletin.

(3) If any discrepancy is detected that

cannot be repaired within the limits specified

in the service bulletin, prior to further flight,

repair in accordance with a method approved

by the Manager, International Branch, ANM–

116, FAA, Transport Airplane Directorate.

Note 2: Accomplishment of the terminating

actions required by paragraph (b) of this AD

in accordance with Messier-Dowty Service

Bulletin F100–32–86, including Appendix A

and Appendix B; all Revision 1, all dated

November 1, 1996; prior to the effective date

of this AD, is acceptable for compliance with

the requirements of this paragraph.

(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,

International Branch, ANM–116. 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.

(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) Except as provided by paragraph (b)(3)

of this AD, the actions shall be done in

accordance with Messier-Dowty Service

Bulletin F100–32–86, Revision 2, dated July

3, 1997, including Appendix A, Revision 1,

dated November 1, 1996, and Appendix B,

Revision 1, dated November 1, 1996, which

contains the following list of effective pages:

Page No.

Revision

level

shown

on

page

Date shown on

page

1, 5, 6 ............ 2 July 3, 1997.

2–4, 7–17 ...... 1 November 1, 1996.

Appendix A

1–3 ................ 1 November 1, 1996.

Appendix B

1–5 ................ 1 November 1, 1996.

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 Fokker Services B.V., Technical

Support Department, P.O. Box 75047, 1117

ZN Schiphol Airport, the Netherlands; or

from Messier-Dowty Ltd., Cage: K0654,

Cheltenham Road, Gloucester, GL2 9QH,

England. 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 Dutch airworthiness directive 1996–133/

2(A), dated January 31, 1997.

(f) This amendment becomes effective on

July 30, 1998.

Issued in Renton, Washington, on June 16,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–16498 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–145–AD; Amendment

39–10622; AD 98–13–31]

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

repetitive visual inspections to detect

discrepancies of the bushing installation

of the aileron actuation fitting, and

eventual installation of staked bushings

in the fitting. Accomplishment of such

installation terminates the repetitive

inspections. This amendment also

provides for an optional temporary

preventive action, which, if

accomplished, would allow the

repetitive inspection intervals to be

extended until the terminating action is

accomplished. 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 fitting

lugs due to vibration caused by loose

bushings in the fittings, and consequent

reduced controllability of the airplane.

DATES: Effective July 30, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 30,

1998.

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