Federal Register / Vol. 62, No. 36 / Monday, February 24, 1997 / Rules and Regulations 8157

not pose a serious burden on any

operator.

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

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 34 Fokker

Model F27 series airplanes of U.S.

registry will be affected by this AD.

It will take approximately 2 work

hours per airplane to accomplish the

required actions, at an average labor rate

of $60 per work hour. Based on these

figures, the cost impact of this AD on

U.S. operators is estimated to be $4,080,

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.

However, the FAA has been advised

that one U.S. operator already has

accomplished the required actions on its

2 affected airplanes. Therefore, the

future cost impact of this AD is only

$4,056.

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:

97–04–16 Fokker: Amendment 39–9941.

Docket 96-NM–38-AD.

Applicability: Model F27 series airplanes,

serial numbers 10102 through 10692

inclusive; equipped with Walter Kidde nose

wheel steering system (steering unit gearbox

housing assembly) having part number

893954; 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 a reduction in the torque value

of the bolt in the Walter Kidde nose wheel

steering system, which could result in

reduced controllability of the airplane or the

collapse of the nose landing gear (NLG)

during landing, accomplish the following:

(a) Within 500 flight hours after the

effective date of this AD, or within 4 months

after the effective date of this AD, whichever

occurs first, tighten the bolt that connects the

gearbox housing assembly of the steering unit

to the pivot bracket of the NLG to a torque

value of 700 to 800 inch-pounds, in

accordance with Fokker Service Bulletin

F27/32–166, dated September 7, 1993.

(b) Within 30 days following

accomplishment of paragraph (a) of this AD,

revise the FAA-approved maintenance

program to include periodic inspections of

the torque value of the affected bolt, as

described in Fokker F27 Maintenance

Circular No. 32–6, dated April 30, 1993; and,

thereafter, comply with those requirements.

Note 2: Once the maintenance program is

changed to include the required periodic

inspections, in accordance with this

paragraph, operators do not need to make a

maintenance log entry to show compliance

with this AD every time those inspections are

accomplished thereafter.

(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 3: 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 actions shall be done in accordance

with Fokker Service Bulletin F27/32–166,

dated September 7, 1993; and Fokker F27

Maintenance Circular No. 32–6, dated April

30, 1993. 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

March 31, 1997.

Issued in Renton, Washington, on February

13, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–4201 Filed 2–21–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–48–AD; Amendment

39–9942; AD 97–04–17]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace Model BAe 146 Series

Airplanes and Model Avro 146–RJ

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.
8158 Federal Register / Vol. 62, No. 36 / Monday, February 24, 1997 / Rules and Regulations

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain British Aerospace

Model BAe 146 series airplanes and

Model Avro 146–RJ series airplanes,

that requires inspections to detect

leakage of hydraulic fluid from the lock

jack assemblies of the main landing gear

(MLG), and eventual replacement of

those assemblies with new or

serviceable assemblies. This amendment

is prompted by reports of leakage of

hydraulic fluid from lock jack

assemblies due to a manufacturing

forging defect that extends through the

wall of the lock jack assembly. The

actions specified by this AD are

intended to prevent leakage of hydraulic

fluid from the lock jack assemblies of

the MLG, which, in conjunction with a

hot brake, could cause a fire in the MLG

bay.

DATES: Effective March 31, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 31,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from British Aerospace Holding, Inc.,

Avro International Aerospace Division,

P.O. Box 16039, Dulles International

Airport, Washington, DC 20041–6039.

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

Backman, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2797; 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 British

Aerospace Model BAe 146 series

airplanes and Model Avro 146–RJ series

airplanes was published in the Federal

Register on August 27, 1996 (61 FR

44006). That action proposed to require

an inspection to identify affected lock

jack assemblies by serial number. That

action also proposed to require

repetitive inspections of certain lock

jack assemblies to detect leakage of

hydraulic fluid from the lock jack

assemblies, and, if leakage is detected,

replacement of the lock jack assemblies

with new or serviceable assemblies.

That action also proposed to require

eventual replacement of the lock jack

assemblies with new or serviceable

assemblies.

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 52 airplanes

of U.S. registry will be affected by this

AD.

To accomplish the required

inspections will take approximately 1

work hour per airplane, per inspection,

at an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of the required inspections on

U.S. operators is estimated to be $3,120,

or $60 per airplane, per inspection

cycle.

To accomplish the required

replacement of the lock jack assembly

will take approximately 1 work hour per

airplane, at an average labor rate of $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 required

replacement on U.S. operators is

estimated to be $3,120, or $60 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:

97–04–17 British Aerospace Regional

Aircraft Limited, AVRO International

Aerospace Division (formerly British

Aerospace, plc; British Aerospace

Commercial Aircraft Limited):

Amendment 39–9942. Docket 96–NM–

48–AD.

Applicability: Model BAe 146 series

airplanes and Model Avro 146–RJ series

airplanes having lock jack assemblies of the

main landing gear as listed in British

Aerospace Inspection Service Bulletin SB

32–103, Revision 1, dated February 22, 1991;

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 prevent leakage of hydraulic fluid from

the lock jack assemblies of the main landing

gear (MLG), which, in conjunction with a hot

brake, could cause a fire in the MLG bay;

accomplish the following:
Federal Register / Vol. 62, No. 36 / Monday, February 24, 1997 / Rules and Regulations 8159

(a) Within 30 days after the effective date

of this AD, verify the serial number of all

lock jack assemblies, part number

104275001, of the MLG.

Note 2: Verification may be accomplished

by a review of appropriate records.

(1) If no lock jack assembly has a serial

number as listed in British Aerospace

Inspection Service Bulletin SB 32–103,

Revision 1, dated February 22, 1991, no

further action is required by this paragraph.

(2) If any lock jack assembly has a serial

number as listed in British Aerospace

Inspection Service Bulletin SB 32–103,

Revision 1, dated February 22, 1991, prior to

further flight, perform a visual inspection to

detect any leakage of hydraulic fluid from the

lock jack assembly, in accordance with the

service bulletin.

(i) If no leakage of hydraulic fluid is

detected, thereafter, repeat the inspection at

intervals not to exceed 30 days, until the

requirements of paragraph (b) of this AD are

accomplished.

(ii) If any leakage of hydraulic fluid is

detected, prior to further flight, replace the

lock jack assembly with a new or serviceable

unit that does not have one of those serial

numbers, in accordance with the service

bulletin.

(b) Within 6 months after the effective date

of this AD, replace any lock jack assembly

having a serial number listed in British

Aerospace Inspection Service Bulletin SB

32–103, Revision 1, dated February 22, 1991,

with a new or serviceable assembly that does

not have one of those serial numbers, in

accordance with the service bulletin.

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

person shall install a lock jack assembly,

having any serial number listed in British

Aerospace Inspection Service Bulletin SB

32–103, Revision 1, dated February 22, 1991,

on any airplane.

(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,

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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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) The inspections and replacements shall

be done in accordance with British

Aerospace Inspection Service Bulletin SB

32–103, Revision 1, dated February 22, 1991,

which contains the specified list of effectives

pages:

Page No.

Revision

level

shown on

page

Date shown

on page

1, 2, Appendix

A1, Page 1–3.

1 Feb. 22,

1991.

3, Appendix A1,

Page 4.

Original June 15,

1990.

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 British Aerospace Holding, Inc., Avro

International Aerospace Division, P.O. Box

16039, Dulles International Airport,

Washington, DC 20041–6039. 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

March 31, 1997.

Issued in Renton, Washington, on February

13, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–4200 Filed 2–21–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–142–AD; Amendment

39–9943; AD 97–04–18]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F27 Mark 100, 200, 300, 400, 500,

600, and 700 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Fokker Model F27

Mark 100, 200, 300, 400, 500, 600, and

700 series airplanes, that requires

repetitive x-ray inspections to detect

cracks in stringers 4 through 7 of the

lower skin of the wings, and

modification or repair, if necessary. This

amendment also requires modification

of the stringers of the lower skin of the

wings, which terminates the repetitive

inspections. This amendment is

prompted by reports of fatigue cracking

found in stringers 4 through 7 of the

lower skin of the wings. The actions

specified by this AD are intended to

prevent such fatigue cracking, which

could result in reduced structural

integrity of the wings.

DATES: Effective March 31, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 31,

1997.

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:

Ruth Harder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–1721; 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 Fokker Model F27

Mark 100, 200, 300, 400, 500, 600, and

700 series airplanes was published in

the Federal Register on August 6, 1996

(61 FR 40760). That action proposed to

require repetitive x-ray inspections to

detect cracks of stringers 4 through 7,

inclusive, at certain wing stations of the

lower skin of the wings; and

modification or repair, if necessary.

That action also proposed to require

modification of certain stringers of the

lower skin of the wings, which, when

accomplished, would constitute

terminating action for the repetitive

inspection requirements.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Support for the Proposal

One commenter supports the

proposed AD.

Request to Extend Proposed

Compliance Time

One commenter requests that the

proposal be revised to extend the

compliance time for the initial x-ray

inspection (Part 2 of the Fokker Service

Bulletin F27/57–70)) and the

terminating modification (Part 1 of the

Fokker service bulletin) to the next

regularly scheduled ‘‘C’’ check. This

commenter states that the 12-month

compliance time for the inspection

creates unnecessary burdens both

economically and operationally.

However, since the downtime for

accomplishing the terminating action