Federal Register / Vol. 62, No. 193 / Monday, October 6, 1997 / Proposed Rules 52053

12612, it is determined that this

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting 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.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

De Havilland, Inc.: Docket 97–NM–120–AD.

Applicability: Model DHC–8–100, –200,

and –300 series airplanes; as listed in

Bombardier Alert Service Bulletin S.B. A8–

28–20, Revision ‘A,’ dated September 10,

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

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 (f) 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 fuel leaks and consequent

increased risk of engine fires, accomplish the

following:

(a) Within 30 days after the effective date

of this AD, inspect the five refuel/defuel tube

assemblies in the engine nacelles to detect

fuel leaks, in accordance with Part 1 of the

Accomplishment Instructions of Bombardier

Alert Service Bulletin S.B. A8–28–20,

Revision ‘A’, dated September 10, 1996. If

any fuel leak is found, prior to further flight,

replace the refuel/defuel tube assembly with

an improved assembly, in accordance with

the alert service bulletin. Thereafter, repeat

the inspection at intervals not to exceed 6

months.

(b) Within 12 months after the effective

date of this AD, modify the refuel/defuel tube

assembly located under the exhaust

fingernail on the engine nacelle, as specified

in Part 2 of the Accomplishment Instructions

of Bombardier Alert Service Bulletin S.B.

A8–28–20, Revision ‘A,’ dated September 10,

1996, in accordance with the procedures

specified in the alert service bulletin.

(c) Within 24 months after the effective

date of this AD, modify the remaining refuel/

defuel tube assemblies, as specified in Part 3

of the Accomplishment Instructions of

Bombardier Alert Service Bulletin S.B. A8–

28–20, Revision ‘A,’ dated September 10,

1996, in accordance with the procedures

specified in the alert service bulletin.

(d) Accomplishment of the modifications

required by paragraphs (b) and (c) of this AD

constitutes terminating action for the

repetitive inspections required by paragraph

(a) of this AD.

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

person shall install a refuel/defuel tube

assembly having part number 82820107–007,

82821015–003, 82820108–005, 82820245–

001, 82820246–001, 82820247–001, or

82821014–001, on any airplane.

(f) 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, New York

Aircraft Certification Office (ACO), FAA,

Engine and Propeller Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, New York ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

(g) Special flight permits may be issued in

accordance with § 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.

Note 3: The subject of this AD is addressed

in Canadian airworthiness directive CF–96–

14, dated August 20, 1996.

Issued in Renton, Washington, on

September 30, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–26376 Filed 10–3–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–106–AD]

Airworthiness Directives; Short

Brothers Model SD3–60 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to all

Short Brothers Model SD3–60 series

airplanes. This proposal would require

repetitive inspections to detect

corrosion and/or wear of the top and

bottom shear decks of the left and right

stub wings in the area of the forward

pintle pin of the main landing gear

(MLG), and repair, if necessary. This

proposal is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by the proposed AD are

intended to detect and correct corrosion

and/or wear of the top and bottom shear

decks of the left and right stub wings in

the area of the forward pintle pin of the

MLG, which could result in failure of

the MLG to extend or retract.

DATES: Comments must be received by

November 5, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

106–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 p.m.,

Monday through Friday, except Federal

holidays.

The service information referenced in

the proposed rule may be obtained from

Short Brothers, Airworthiness &

Engineering Quality, P.O. Box 241,

Airport Road, Belfast BT3 9DZ,

Northern Ireland. This information may

be examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

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

(425) 227–1112; fax (425) 227–1149.
52054 Federal Register / Vol. 62, No. 193 / Monday, October 6, 1997 / Proposed Rules

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 97–NM–106–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

97–NM–106–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Civil Aviation Authority (CAA),

which is the airworthiness authority for

the United Kingdom, notified the FAA

that an unsafe condition may exist on

all Short Brothers Model SD3–60 series

airplanes. The CAA advises that it has

received reports of corrosion and/or

wear of the top and bottom shear decks

of the left and right stub wings in the

area of the forward pintle pin of the

main landing gear (MLG). The corrosion

and/or wear was attributed to migration

of the retaining pin of the forward pintle

pin of the MLG due to loss of the

retaining pin’s circlip. Such corrosion or

wear of the top and bottom shear decks

of the left and right stub wings in the

area of the forward pintle pin of the

MLG, if not detected and corrected in a

timely manner, could result in failure of

the MLG to extend or retract.

Explanation of Relevant Service

Information

Short Brothers has issued Service

Bulletin SD360–53–42, dated September

1996, which describes procedures for

repetitive inspections to detect

corrosion and/or wear of the top and

bottom shear decks of the left and right

stub wings in the area of the forward

pintle pin of the MLG, and repair, if

necessary. For airplanes on which

certain depths of corrosion or wear is

detected, the service bulletin describes

procedures for a visual inspection to

detect any discrepancy of the pintle pin

and sleeve. The CAA classified this

service bulletin as mandatory and

issued British airworthiness directive

005–09–96 in order to assure the

continued airworthiness of these

airplanes in the United Kingdom.

FAA’s Conclusions

This airplane model is manufactured

in the United Kingdom and is type

certificated for operation in the United

States under the provisions of § 21.29 of

the Federal Aviation Regulations (14

CFR 21.29) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the CAA has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the CAA,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design, the proposed AD would

require repetitive inspections to detect

and correct corrosion and/or wear of the

top and bottom shear decks of the left

and right stub wings in the area of the

forward pintle pin of the MLG, and

repair of any corrosion and/or wear.

Those actions are required to be

accomplished in accordance with the

service bulletin described previously.

Differences Between the Proposal and

the related CAA AD

Operators should note that for certain

depths of corrosion and/or wear

detected that require an inspection of

the pintle pin and sleeve, this AD

requires the repair of any discrepancy of

the pintle pin or sleeve to be

accomplished in accordance with a

method approved by the FAA.

Cost Impact

The FAA estimates that 88 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 13 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $68,640, or $780 per

airplane.

The total cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed 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 proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

Is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting 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.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:
Federal Register / Vol. 62, No. 193 / Monday, October 6, 1997 / Proposed Rules 52055

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:

Short Brothers, PLC: Docket 97-NM–106-AD.

Applicability: All Model SD3–60 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

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 use the authority

provided in paragraph (c) of this AD 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 airplane from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent failure of the main landing gear

(MLG) to extend or retract due to corrosion

and/or wear of the left and right stub wings

in the area of the forward pintle pin of the

MLG, accomplish the following:

(a) Within 90 days after the effective date

of this AD, conduct an inspection for

corrosion of the top and bottom shear decks

of the left and right stub wings in the area

of the forward pintle pin of the MLG, and

measure the retaining pin holes of the pintle

pin for wear; in accordance with Part A. of

the Accomplishment Instructions of Short

Brothers Service Bulletin SD360–53–42,

dated September 1996.

(1) If any corrosion, wear, or measurement

of the holes for the retaining pin of the pintle

pin is found that is within the limits

specified in Part A. of the Accomplishment

Instructions of the service bulletin, prior to

further flight, repair the discrepancy in

accordance with the service bulletin.

Thereafter, repeat the inspection required by

paragraph (a) of this AD at intervals not to

exceed 6 months.

(2) If any corrosion, wear, or measurement

of the holes for the retaining pin of the pintle

pin is found that is beyond the limits

specified in Part A. of the Accomplishment

Instructions of the service bulletin, prior to

further flight, perform the actions required by

paragraph (a)(2)(i) and (a)(2)(ii) of this AD.

(i) Remove the corrosion and install

bushings on the upper and lower shear webs

in the retaining pin holes for the pintle pin

in accordance with Part B. (left MLG) and/

or Part C. (right MLG), as applicable, of the

Accomplishment Instructions of the service

bulletin.

(ii) Perform a visual inspection of the

pintle pin and the sleeve for any discrepancy,

in accordance with Part B. and/or Part C., as

applicable, of the Accomplishment

Instructions of the service bulletin.

(A) If no discrepancy is detected, the pintle

pin and the sleeve of the pintle pin may be

returned to service.

(B) If any discrepancy of the pintle pin and

sleeve is detected, prior to further flight,

repair the pintle pin and sleeve in

accordance with a method approved by the

Manager, Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate.

(b) Removal of corrosion and installation of

bushings in accordance with Part B. and/or

Part C., as applicable, of the Accomplishment

Instructions of Short Brothers Service

Bulletin SD360–53–42, dated September

1996, constitutes terminating action for the

repetitive inspection requirements 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

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

Special flight permits may be issued in

accordance with §§ 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.

Note 3: The subject of this AD is addressed

in British airworthiness directive 005–09–96.

Issued in Renton, Wash., on September 30,

1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–26377 Filed 10–3–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–45–AD]

RIN 2120–AA64

Airworthiness Directives; Pilatus

Aircraft Ltd. Models PC–12 and PC–12/

45 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to certain Pilatus

Aircraft Ltd. (Pilatus) Models PC–12 and

PC–12/45 airplanes. The proposed

action would require inspecting the

aileron tie-rod jam nuts for looseness,

tightening any loose jam nuts, and

installing a locking sleeve on both ends

of the aileron tie-rod in the chain-drive

of the aileron system. The proposed AD

results from an incident where the

aileron tie-rod jam nuts on the chaindrive of the aileron system became

loose. This caused a differential of

aileron control between the pilot’s

control wheel and the co-pilot’s control

wheel. The actions specified by the

proposed AD are intended to prevent

such aileron control differential caused

by the aileron tie-rod jam nuts becoming

loose, which could result in loss of

aileron control and consequent loss of

control of the airplane.

DATES: Comments must be received on

or before November 7, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 97-CE–45-

AD, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106. Comments

may be inspected at this location

between 8 a.m. and 4 p.m., Monday

through Friday, holidays excepted.

Service information that applies to the

proposed AD may be obtained from

Pilatus Aircraft Ltd., CH–6370 Stans,

Switzerland. This information also may

be examined at the Rules Docket at the

address above.

FOR FURTHER INFORMATION CONTACT: Mr.

Roman T. Gabrys, Aerospace Engineer,

Small Airplane Directorate, Airplane

Certification Service, FAA, 1201

Walnut, suite 900, Kansas City, Missouri

64106; telephone (816) 426–6932;

facsimile (816) 426–2169.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications

should identify the Rules Docket

number and be submitted in triplicate to

the address specified above. All

communications received on or before

the closing date for comments, specified

above, will be considered before taking

action on the proposed rule. The

proposals contained in this notice may

be changed in light of the comments

received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of