47754 Federal Register / Vol. 62, No. 176 / Thursday, September 11, 1997 / Rules and Regulations

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:

97–19–01 SAAB Aircraft AB: Amendment

39–10121. Docket 96–NM–220–AD.

Applicability: Model SAAB 2000 series

airplanes, serial numbers –004 through –030

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

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 damage to the hydraulic tubes

and electrical harnesses, which could lead to

failure of the number 2 hydraulic system or

loss of certain electrical and landing systems,

and resultant reduced controllability of the

airplane, accomplish the following:

(a) Within 60 days after the effective date

of this AD, perform a one-time visual

inspection of the hydraulic tubes and

electrical harness wires of the wing rear

access door for chafing, leakage, or wear

damage; in accordance with paragraph B. of

the Accomplishment Instructions of Saab

Service Bulletin 2000–53–010, Revision 01,

dated October 10, 1995.

(1) If any chafing or leakage of the

hydraulic tubes is detected, prior to further

flight, repair in accordance with a method

approved by the Manager, Standardization

Branch, ANM–113, FAA, Transport Airplane

Directorate.

(2) If any damage to the metal braid or wire

insulation is detected, prior to further flight,

repair in accordance with paragraph E. of the

Accomplishment Instructions of Saab Service

Bulletin 2000–53–010, Revision 01, dated

October 10, 1995.

(b) Within 60 days after the effective date

of this AD, modify the wing rear access door

and apply silicon tape to the electrical

harnesses, in accordance with paragraph C.

of the Accomplishment Instructions of Saab

Service Bulletin 2000–53–010, Revision 01,

dated October 10, 1995.

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

person shall install wing rear access doors,

part numbers 7353500–713/–714 or

7353500–715/–716, on any airplane, unless

the part has been modified in accordance

with Saab Service Bulletin 2000–53–010,

Revision 01, dated October 10, 1995.

(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.

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.

(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 inspection, modification, and

certain repairs shall be done in accordance

with Saab Service Bulletin 2000–53–010,

Revision 01, dated October 10, 1995. 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.

(g) This amendment becomes effective on

October 16, 1997.

Issued in Renton, Washington, on

September 3, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–23858 Filed 9–10–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94–SW–28–AD; Amendment

39–10129; AD 97–19–09]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron, Inc. Model 214ST

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Bell Helicopter Textron,

Inc. (BHTI) Model 214ST helicopters,

that requires creation of a component

history card or equivalent record using

a Retirement Index Number (RIN)

system; establishes a system for tracking

increases to the accumulated RIN; and

establishes a maximum accumulated

RIN for the pillow block bearing bolts

(bearing bolts). This amendment is

prompted by fatigue analyses and tests

that show certain bearing bolts fail

sooner than originally anticipated

because of the unanticipated high

number of takeoffs and external load

lifts utilizing high-power settings in

addition to the time-in-service (TIS)

accrued under other operating

conditions. The actions specified by this

AD are intended to prevent fatigue

failure of the bearing bolts, which could

result in failure of the main rotor system

and subsequent loss of control of the

helicopter.

EFFECTIVE DATE: October 16, 1997.

FOR FURTHER INFORMATION CONTACT: Mr.

Charles Harrison, Aerospace Engineer,

FAA, Rotorcraft Certification Office,

Rotorcraft Directorate, Fort Worth,

Texas 76193–0170, telephone (817)

222–5447, fax (817) 222–5959.

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 BHTI Model 214ST

helicopters was published in the

Federal Register on December 23, 1996

(61 FR 67503). That action proposed to

require creation of a component history
Federal Register / Vol. 62, No. 176 / Thursday, September 11, 1997 / Rules and Regulations 47755

card using a RIN system; establishing a

system for tracking increases to the

accumulated RIN; and establishing a

maximum accumulated RIN for the

bearing bolts.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule with three non-substantive

changes. The words ‘‘based on

condition’’ were deleted from paragraph

(d) of the AD. If any of the four bearing

bolts are replaced for any reason, all

four bearing bolts must be replaced. The

words ‘‘or equivalent record’’ are added

to paragraphs (b) and (c). The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

The FAA estimates that 6 helicopters

of U.S. registry will be affected by this

AD, that it will take approximately (1)

24 work hours per helicopter to replace

the affected bearing bolts due to the new

method of determining the retirement

life required by this AD; (2) 2 work

hours per helicopter to create the

component history card or equivalent

record (record); (3) 10 work hours per

helicopter to maintain the record each

year, and that the average labor rate is

$60 per work hour. Required parts will

cost approximately $2,000 per

helicopter. Based on these figures, the

total cost impact of the AD on U.S.

operators for the first year is estimated

to be $7,760 and each subsequent year

to be $7,160. These costs assume

replacement of the bearing bolts in onesixth of the fleet each year, creation and

maintenance of the records for all the

fleet the first year, and creation of onesixth of the fleet’s records and

maintenance of the records for all the

fleet each subsequent year.

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, 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 a new airworthiness directive to

read as follows:

97–19–09 Bell Helicopter Textron Inc.:

Amendment 39–10129. Docket No. 94–

SW–28–AD.

Applicability: All Model 214ST helicopters

with pillow block bearing bolts (bearing

bolts), part number (P/N) 20–057–12–48D or

–50D, installed, certificated in any category.

Note 1: This AD applies to each helicopter

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

helicopters that have been modified, altered,

or repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (e) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any helicopter

from the applicability of this AD.

Compliance: Required within 25 hours

time-in-service (TIS) after the effective date

of this AD, unless accomplished previously.

To prevent fatigue failure of the bearing

bolts, which could result in failure of the

main rotor system and subsequent loss of

control of the helicopter, accomplish the

following:

(a) Create a component history card or an

equivalent record for the bearing bolts, P/N

20–057–12–48D or –50D.

(b) To determine the accumulated

Retirement Index Number (RIN) to date on

parts in service, multiply the factored flight

hour total to date by 13.6 (round-off the

result to the next higher whole number).

Record on the component history card or

equivalent record the accumulated RIN.

Note 2: Bell Helicopter Textron, Inc. Alert

Service Bulletin 214ST–94–69, dated

November 7, 1994, pertains to this AD.

(c) After compliance with paragraphs (a)

and (b) of this AD, during each operation

thereafter, maintain a count of each takeoff

and external load lift performed, and at the

end of each day’s operations, increase the

accumulated RIN on the component history

cards or equivalent record as follows:

(1) Increase the RIN by 2 for each takeoff.

(2) Increase the RIN by 2 for each external

load lift, or increase the RIN by 4 for each

external load lift operation in which the load

is picked up at a higher elevation and

released at a lower elevation, and the

difference in elevation between the pickup

point and the release point is 200 feet or

greater.

(d) Remove the bearing bolts from service

on or before attaining an accumulated RIN of

17,000. If any of the four bearing bolts are

replaced, then all four bolts must be replaced

at that time. The bolts are no longer retired

based upon flight hours. This AD revises the

Airworthiness Limitations section of the

maintenance manual by establishing a new

retirement life for the bearing bolts of 17,000

RIN.

(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, Rotorcraft

Certification Office, FAA, Rotorcraft

Directorate. Operators shall submit their

requests through an FAA Principal

Maintenance Inspector, who may concur or

comment and then send it to the Manager,

Rotorcraft Certification Office.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Certification

Office.

(f) 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 helicopter

to a location where the requirements of this

AD can be accomplished.

(g) This amendment becomes effective on

October 16, 1997.

Issued in Fort Worth, Texas, on September

5, 1997.

Larry M. Kelly,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–24117 Filed 9–10–97; 8:45 am]

BILLING CODE 4910–13–P