54366 Federal Register / Vol. 62, No. 202 / Monday, October 20, 1997 / Rules and Regulations

(2) Contents of request for waiver. A

request for a waiver or reduction of fees

shall include:

(i) A clear statement of the requester’s

interest in the documents;

(ii) The use proposed for the

documents and whether the requester

will derive income or other benefit for

such use;

(iii) A statement of how the public

will benefit from such use and from the

Board’s release of the documents;

(iv) A description of the method by

which the information will be

disseminated to the public; and

(v) If specialized use of the

information is contemplated, a

statement of the requester’s

qualifications that are relevant to that

use.

(3) Burden of proof. The burden shall

be on the requester to present evidence

or information in support of a request

for a waiver or reduction of fees.

(4) Determination by Secretary. The

Secretary shall make a determination on

the request for a waiver or reduction of

fees and shall notify the requester

accordingly. A denial may be appealed

to the Board in accordance with

§ 261.13(j).

(g) Employee requests. In connection

with any request by an employee,

former employee, or applicant for

employment, for records for use in

prosecuting a grievance or complaint of

discrimination against the Board, fees

shall be waived where the total charges

(including charges for information

provided under the Privacy Act of 1974

(5 U.S.C. 552a) are $50 or less; but the

Secretary may waive fees in excess of

that amount.

(h) Special services. The Secretary

may agree to provide, and set fees to

recover the costs of, special services not

covered by the Freedom of Information

Act, such as certifying records or

information and sending records by

special methods such as express mail or

overnight delivery.

APPENDIX A TO § 261.17.—FREEDOM

OF INFORMATION FEE SCHEDULE

Duplication:

Photocopy, per standard page .... $0.10

Paper copies of microfiche, per

frame ........................................ .10

Duplicate microfiche, per microfiche ......................................... .35

Search and review:

Clerical/Technical, hourly rate ..... 20.00

Professional/Supervisory, hourly

rate ........................................... 38.00

Manager/Senior Professional,

hourly rate ................................ 65.00

Computer search and production:

Computer operator search, hourly rate ....................................... 32.00

APPENDIX A TO § 261.17.—FREEDOM

OF INFORMATION FEE SCHEDULE—

Continued

Tapes (cassette) per tape ........... 6.00

Tapes (cartridge), per tape ......... 9.00

Tapes (reel), per tape ................. 18.00

Diskettes (31⁄2′′), per diskette ..... 4.00

Diskettes (51⁄4′′), per diskette ..... 5.00

Computer Output (PC), per

minute ...................................... .10

Computer Output (mainframe) .... (1)

1Actual cost.

By order of the Board of Governors of the

Federal Reserve System, October 10, 1997.

William W. Wiles,

Secretary of the Board.

[FR Doc. 97–27566 Filed 10–17–97; 8:45 am]

BILLING CODE 6210–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–137–AD; Amendment

39–10159; AD 97–21–06]

RIN 2120–AA64

Airworthiness Directives;

Construcciones Aeronauticas, S.A.

(CASA) Model CN–235 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain CASA Model CN–

235 series airplanes, that requires

repetitive inspections of the torsion

tubes and fittings of the elevator and

rudder assemblies to detect stress

corrosion cracking, and replacement of

cracked parts. This action also requires

accomplishment of a modification that

constitutes terminating action for the

repetitive inspections. This amendment

is prompted by reports indicating that

stress corrosion cracking in these parts

has been found on some airplanes. The

actions specified by this AD are

intended to prevent loss of control of

the elevator and/or rudder, due to

failure of the elevator and/or rudder

assemblies as a result of stress corrosion

cracking.

DATES: Effective November 24, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

24, 1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Construcciones Aeronauticas, S.A.,

Getafe, Madrid, Spain. 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: Greg

Dunn, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2799; 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 CASA

Model CN–235 series airplanes was

published in the Federal Register on

February 7, 1997 (62 FR 5785). That

action proposed to require repetitive

inspections of the torsion tubes and

fittings of the elevator and rudder

assemblies to detect stress corrosion

cracking, and replacement of discrepant

parts. In addition, that action proposed

to require eventual installation of newly

designed torsion tube assemblies on all

airplanes, which, when accomplished,

would constitute terminating action for

the required inspections.

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 1 CASA

Model CN–235 series airplane of U.S.

registry will be affected by this AD.

It will take approximately 6 work

hours per airplane to accomplish each

required visual inspection, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

required inspection on the single

affected U.S. operator is estimated to be

$360, per inspection cycle.

It will take approximately 40 work

hours to accomplish the required

terminating modification, at an average

labor rate of $60 per work hour. (The

work hour figure does not include the

time needed for preparation of the

airplane or equipment; familiarization

with the service bulletin; curing times

for adhesive, sealant, paint, etc.; tool
Federal Register / Vol. 62, No. 202 / Monday, October 20, 1997 / Rules and Regulations 54367

collection; or down time). Required

parts will cost approximately $8,900 per

airplane. Based on these figures, the cost

impact of the required modification on

the single affected U.S. operator is

estimated to be $11,300.

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:

97–21–06 CASA: Amendment 39–10159.

Docket 96–NM–137–AD.

Applicability: CASA Model CN–235

airplanes; as listed in CASA Service Bulletin

SB–235–27–05, Revision 1, dated September

29, 1993 (non-military airplanes), and CASA

Service Bulletin SB–235–27–05M, Revision

2, dated January 25, 1996 (military 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

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 loss of control of the elevator

and/or rudder, due to failure of the elevator

and/or rudder assemblies as a result of stress

corrosion cracking in the torsion tubes and

fittings, accomplish the following:

Note 2: Actions required by this AD that

were accomplished previous to the effective

date of this AD, and in accordance with

earlier versions of the specified CASA service

bulletins, are considered acceptable for

compliance with the applicable requirements

of this AD.

(a) At the applicable time specified in

either paragraph (a)(1) or (a)(2) of this AD,

conduct a visual inspection of the torsion

(torsion) tubes on the elevator and rudder

assemblies to detect stress corrosion

cracking, in accordance with CASA Service

Bulletin SB–235–27–05, Revision 1, dated

September 29, 1993 (for non-military

airplanes) or CASA Service Bulletin SB–235–

27–05M, Revision 2, dated January 25, 1996

(for military airplanes), as applicable.

(1) For airplanes that have accumulated

more than 600 total hours time-in-service, or

more than 1,000 total landings, as of the

effective date of this AD: Conduct the

inspection required by paragraph (a) of this

AD prior to the accumulation of 50 hours

time-in-service, or 100 landings, or within 3

months, after the effective date of this AD,

whichever occurs first.

(2) For all other airplanes: Conduct the

inspection required by paragraph (a) of this

AD prior to the accumulation of 600 total

hours time-in-service, or 1,000 total landings,

or within 6 months, after the effective date

of this AD, whichever occurs first.

(b) If no cracking is detected during the

inspection required by paragraph (a) of this

AD, repeat that inspection at intervals not to

exceed 600 hours time-in-service, or 1,000

landings, or 6 months, whichever occurs

first.

(c) If any cracking is detected during the

inspection required by paragraph (a) of this

AD, prior to further flight, accomplish either

paragraph (c)(1) or (c)(2) of this AD.

(1) Replace cracked parts with a new parts

of the original design, in accordance with the

service bulletin. After replacement, repeat

the visual inspection required by paragraph

(a) of this AD at intervals not to exceed 600

hours time-in-service, or 1,000 landings, or 6

months, whichever occurs first. OR

(2) Replace cracked parts with a newlydesigned parts, in accordance with CASA

Service Bulletin SB–235–27–05, Revision 1,

dated September 29, 1993 (for non-military

airplanes); or CASA Service Bulletin SB–

235–27–05M, Revision 2, dated January 25,

1996 (for military airplanes); as applicable.

This replacement constitutes terminating

action for the repetitive visual inspections of

that part required by paragraph (b) of this

AD.

(d) Within 2 years after the effective date

of this AD, replace all original design parts

comprising the torsion tube assemblies on

the elevator and rudder assemblies with

newly-designed parts, in accordance with

CASA Service Bulletin SB–235–27–05,

Revision 1, dated September 29, 1993 (for

non-military airplanes); or CASA Service

Bulletin SB–235–27–05M, Revision 2, dated

January 25, 1996 (for military airplanes); as

applicable. This action constitutes

terminating action for the inspection

requirements of this AD.

(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,

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.

(f) Special flight permits may be issued in

accordance with sections 21.197 and P21.199

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 actions shall be done in accordance

with CASA Service Bulletin SB–235–27–05,

Revision 1, dated September 29, 1993; and

CASA Service Bulletin SB–235–27–05M,

Revision 2, dated January 25, 1996; as

applicable; which contain the specified

effective pages:
54368 Federal Register / Vol. 62, No. 202 / Monday, October 20, 1997 / Rules and Regulations

Service bulletin referenced and date Page No.

Revision

level

shown on

page

Date shown on

page

SB–235–27–05, Revision 1, September 29, 1993 ................................................................................ 1, 2 ........ 1 .............. September 29,

1993.

3–23 ....... Original .... February 5,

1993.

SB–235–27–05M, Revision 2, January 25, 1996 .................................................................................. 1 ............. 2 .............. January 25,

1996.

2–23 ....... Original .... October 28,

1991.

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 Construcciones Aeronauticas, S.A.,

Getafe, Madrid, Spain. 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 Spanish airworthiness directive 06/94,

dated August 1994.

(h) This amendment becomes effective on

November 24, 1997.

Issued in Renton, Washington, on October

8, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–27222 Filed 10–17–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–274–AD; Amendment

39–10158; AD 97–21–05]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Model DH.125–400A; BH.125–400A and

–600A; HS.125–600A and –700A; BAe

125–800A Series Airplanes; and

Hawker 800 and Hawker 800 XP Series

Airplanes Including Military Variants

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Raytheon Model

DH.125–400A; BH.125–400A and

–600A; HS.125–600A and –700A; BAe

125–800A series airplanes; and Hawker

800 and Hawker 800 XP series airplanes

(including military variants C29A,

U125, U125A). This amendment

requires a one-time inspection to

determine if certain high pressure

oxygen hose assemblies are installed,

and, if installed, replacement of those

hose assemblies with new, improved

hose assemblies. This amendment is

prompted by a report that certain high

pressure oxygen hose assemblies are

susceptible to leakage due to those hose

assemblies not meeting design

specifications during manufacturing.

The actions specified by this AD are

intended to prevent leaks in high

pressure oxygen hose assemblies,

which, if not detected and corrected,

could result in insufficient oxygen

available to the passengers or crew if the

cabin pressure altitude should rise to a

level requiring emergency oxygen.

DATES: Effective November 24, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

24, 1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Raytheon Aircraft Company,

Manager Service Engineering, Hawker

Customer Support Department, P.O. Box

85, Wichita, Kansas 67201–0085. 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,

Small Airplane Directorate, Wichita

Aircraft Certification Office, 1801

Airport Road, Room 100, Mid-Continent

Airport, Wichita, Kansas; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Michael Imbler, Aerospace Engineer,

Systems and Propulsion Branch, ACE–

115W, FAA, Small Airplane Directorate,

Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas

67209; telephone (316) 946–4147; fax

(316) 946–4407.

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 Raytheon

Model DH.125–400A; BH.125–400A and

–600A; HS.125–600A and –700A; BAe

125–800A series airplanes; and Hawker

800 and Hawker 800 XP series airplanes

(including military variants C29A,

U125, U125A), was published in the

Federal Register on July 24, 1997 (62 FR

39787). That action proposed to require

a one-time inspection to determine if

certain high pressure oxygen hose

assemblies are installed, and, if

installed, replacement of those hose

assemblies with new, improved hose

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 404 Raytheon

Model DH.125–400A; BH.125–400A and

–600A; HS.125–600A and –700A; BAe

125–800A; and Hawker 800 and Hawker

800 XP series airplanes (including

military variants) of U.S. registry will be

affected by this AD.

It will take approximately 1 work

hour 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 the initial

inspection required by this AD on U.S.

operators is estimated to be $24,240, or

$60 per airplane.

Should an operator be required to

accomplish the replacement, it would

take approximately 1 work hour per

airplane to accomplish it, at an average

labor rate of $60 per work hour.

Required parts would be supplied by

the manufacturer at no cost to the

operators. Based on these figures, the

cost impact of the replacement on U.S.

operators is estimated to be $60 per

airplane.