### 14014 Federal Register / Vol. 61, No. 62 / Friday, March 29, 1996 / Rules and Regulations

series airplanes is estimated to be $2,640, or $60 per airplane.

Should an operator of Model F28 Mark 0100 series airplanes be required to accomplish the necessary bolt replacement, it will take approximately 7 work hours per airplane to accomplish the replacement, at an average labor rate of $60 per work hour. Required parts will cost approximately $100 per airplane. Based on these figures, the cost impact of any necessary replacement action is estimated to be $520 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.

Currently there are no Fokker Model F27 Mark 050 series airplanes on the U.S. Register. However, should an affected airplane be imported and placed on the U.S. Register in the future, it will take approximately 1 work hour per airplane to accomplish the required inspection, at an average labor rate of $60 per work hour. Based on these figures, the impact of the required inspection on operators of Model F27 Mark 050 series airplanes will be $60 per airplane.

Should an operator of Model F27 Mark 050 series airplanes be required to accomplish the necessary bolt replacement, it will take approximately 17 work hours per airplane to accomplish the replacement, at an average labor rate of $60 per work hour. Required parts will cost approximately $150 per airplane. Based on these figures, the cost impact of any necessary replacement action is estimated to be $1,170 per airplane.

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:

96–07–04 Fokker: Amendment 39–9553.
Docket 95–NM–70–AD. Applicability: Model F27 Mark 050 series airplanes having serial numbers 20247 through 20292 inclusive, and 20294 through 20297 inclusive; and Model F28 Mark 0100 series airplanes having serial numbers 11390 through 11479 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 (b) 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 electrical arcing and subsequent loss of the associated electrical system, which could result in the potential for an electrical fire, accomplish the following:

(a) Within 12 months after the effective date of this AD, perform an inspection to verify if adequate clearance exists between the insulation screen and the two adjacent
terminal bolts in accordance with Fokker Service Bulletin SBF100–20–001, dated January 15, 1994 (for Model F28 Mark 0100 series airplanes), or Fokker Service Bulletin SBF50–20–003, dated January 11, 1994 (for Model F27 Mark 050 series airplanes), as applicable.

(1) If adequate clearance is found, no further action is required by this AD.

(2) If inadequate clearance is found, prior to further flight, replace the circuit breaker
terminal bolts with new bolts in accordance with the applicable service bulletin.

(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, 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.

(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.

(d) The inspection and replacement shall
be done in accordance with Fokker Service Bulletin SBF100–20–001, dated January 15, 1994, or Fokker Service Bulletin SBF50–20– 003, dated January 11, 1994, 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. 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.

(e) This amendment becomes effective on April 29, 1996.

Issued in Renton, Washington, on March 21, 1996.
Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 96–7400 Filed 3–28–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 95–NM–86–AD; Amendment 39–9555; AD 96–07–06]

Airworthiness Directives; Fokker Model F28 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 F28 Mark 0100 series airplanes, that requires

### 14015 Federal Register / Vol. 61, No. 62 / Friday, March 29, 1996 / Rules and Regulations

inspection(s) to verify that the position
indicator of the fuel balance transfer valve (FBTV) is in the closed position, and closing the FBTV, if necessary; and
deactivation of the fuel balance transfer system (FBTS). This amendment is prompted by a report that, under certain failure conditions, the actuator of the FBTV could remain in the open position without a flight deck indication. The actions specified by this AD are
intended to ensure that the FBTV is not in the open position during flight,
which could lead to the reduction offuel supply to the engines during crossfeed operation and consequent engine
fuel starvation.

DATES : Effective April 29, 1996.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of April 29,
1996.

ADDRESSES : The service information referenced in this AD may be obtained from Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. 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: Tim Dulin, Aerospace Engineer, Standardization Branch, ANM–113, FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington 98055–4056; telephone (206) 227–2141; fax (206) 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 F28 Mark 0100 series airplanes was published in the Federal Register on December 11, 1995 (60 FR 63470). That action proposed to require inspection(s) to verify that the position
indicator of the fuel balance transfer valve (FBTV) is in the closed position, and closing the FBTV, if necessary; and
deactivation of the fuel balance transfer system (FBTS).

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.

The commenter supports the proposed rule.

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 as proposed.

The FAA estimates that 4 airplanes of U.S. registry will be affected by this AD, that it will take approximately 4 work hours per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Required parts will cost approximately $250 per airplane. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $1,960, or $490 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.

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:

96–07–06 Fokker: Amendment 39–9555.
Docket 95–NM–86–AD. Applicability: Model F28 Mark 0100 series airplanes, as listed in Fokker Service Bulletin SBF100–28–030, Revision 1, dated December 5, 1994; 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 (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 the reduction of fuel supply to the engines during cross-feed operation, which could lead to engine fuel starvation, accomplish the following:

(a) After the effective date of this AD, whenever the fuel balance transfer system (FBTS) is used during maintenance, prior to further flight, perform an inspection to verify that the position indicator of the fuel balance transfer valve (FBTV) is in the closed position, in accordance with Fokker Service Bulletin SBF100–28–030, Revision 1, dated December 5, 1994. The inspection requirements of this paragraph must be accomplished until the deactivation required by paragraph (b) of this AD is accomplished.

(1) If the position indicator is in the closed position, no further action is required by this paragraph.

(2) If the position indicator is in the open position, close the FBTV in accordance with
the service bulletin.

(b) Within 90 days after the effective date of this AD, deactivate the FBTS in
accordance with either Part 2 or Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF100–28–030, Revision 1, dated December 5, 1994, as applicable. Accomplishment of the deactivation constitutes terminating action for the repetitive inspection requirements of paragraph (a) of this AD.

(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

### 14016 Federal Register / Vol. 61, No. 62 / Friday, March 29, 1996 / Rules and Regulations

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 actions shall be done in accordance
with Fokker Service Bulletin SBF100–28– 030, Revision 1, dated December 5, 1994, which contains the following list of effective

pages:

Page No. Revision level shown on

page Date shown
on page

1–3, 5, 8, 10 . 1 ................... December 5,
1994. 4, 6, 7, 9

....... Original

........ August 28,
1994.

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 Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. 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 April 29, 1996.

Issued in Renton, Washington, on March 21, 1996.
Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 96–7399 Filed 3–28–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 95–NM–136–AD; Amendment 39–9554; AD 96–07–05]

Airworthiness Directives; Dornier Model 328–100 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION : Final rule.

SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328–100 series airplanes, that requires
installation of a reinforcement doubler
on the rudder skin. This amendment is prompted by the results of a design review of this airplane model that revealed inadequate structural strength of the attachment fitting of the rudder damper and of the adjacent structure. The actions specified by this AD are intended to prevent failure of the
attachment structure of the rudder damper in the event of aerodynamic gust loads, as the result of inadequate structural strength of the subject

structure.

DATES : Effective April 29, 1996.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of April 29,
1996.

ADDRESSES : The service information referenced in this AD may be obtained from Dornier Luftfahrt GmbH, P.O. Box 1103, D–82230 Wessling, Germany. 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: Gary Lium, Aerospace Engineer, Standardization Branch, ANM–113, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (206) 227–1112; fax (206) 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 Dornier Model 328–100 series airplanes was published in the Federal Register on January 3, 1996 (61 FR 133). That action proposed to require installation of a
reinforcement doubler on the rudder
skin.

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.

The commenter supports the proposed rule.

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 as proposed.

The FAA estimates that 12 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. Required parts will be supplied by the manufacturer at no cost to operators. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $1,440, 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.

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:

96–07–05 Dornier: Amendment 39–9554.
Docket 95–NM–136–AD. Applicability: Model 328–100 series airplanes, serial numbers 3005 through 3024 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