31614 Federal Register / Vol. 63, No. 111 /Wednesday, June 10, 1998 /Rules and Regulations

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:

98–12–25 British Aerospace Regional

Aircraft [Formerly Jetstream Aircraft

Limited; British Aerospace (Commercial

Aircraft) Limited]: Amendment 39–

10579. Docket 97–NM–312–AD.

Applicability: BAe Model ATP airplanes,

constructor’s numbers 2001 through 2063

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 (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 partial seizure of the forward

door of the main landing gear (MLG)

operating mechanism, which could result in

the inability to lower or retract the MLG,

accomplish the following:

(a) Within 300 flight hours or within 90

days after the effective date of this AD,

whichever occurs first, perform a one-time

visual inspection to detect corrosion, wear, or

damage of the operating mechanism of the

forward door of the MLG; and clean,

degrease, and relubricate the door operating

mechanism; in accordance with British

Aerospace Service Bulletin ATP–32–84,

Revision 1, dated September 26, 1997.

(1) If no corrosion, wear, or damage is

detected during the inspection required by

paragraph (a) of this AD, no further action is

required by this AD.

(2) If any corrosion, damage, or worn

component is detected during the inspection

required by paragraph (a) of this AD,

accomplish the requirements of paragraphs

(a)(2)(i) and (a)(2)(ii) of this AD, as

applicable.

(i) If any corrosion or damage is detected,

prior to further flight, repair in accordance

with a method approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate.

(ii) If any worn component is detected,

within 600 flight hours after performing the

inspection required by paragraph (a) of this

AD, replace the component with a new or

serviceable part in accordance with the

service bulletin.

(b) Within 300 flight hours after

accomplishing the inspection required by

paragraph (a) of this AD, perform an

operational inspection to ensure smooth

operation of the spring strut of the forward

door of the MLG, and relubricate the

operating spring and sliding tube of the

forward door ‘A’ frame, in accordance with

British Aerospace Service Bulletin ATP–32–

84, Revision 1, dated September 26, 1997.

(1) Repeat the operational inspections

thereafter at intervals not to exceed 300 flight

hours, until the accumulation of 1,500 flight

hours after the accomplishment of the

inspection required by paragraph (a) of this

AD.

(2) Following the accomplishment of all

inspections required by paragraph (b)(1) of

this AD, repeat the operational inspections

and relubrication required by paragraph (b)

of this AD at intervals not to exceed 1,500

flight hours.

(c) If any discrepancy is detected during

any operational inspection and relubrication

required by paragraph (b) of this AD, prior to

further flight, replace any discrepant part

with a new or serviceable part in accordance

with a method approved by the Manager,

International Branch, ANM–116.

(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,

International Branch, ANM–116. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(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) Except as provided by paragraphs

(a)(2)(i) and (c) of this AD, the actions shall

be done in accordance with British

Aerospace Service Bulletin ATP–32–84,

Revision 1, dated September 26, 1997. 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 AI(R)

American Support, Inc., 13850 Mclearen

Road, Herndon, Virginia 20171. 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

July 15, 1998.

Issued in Renton, Washington, on June 3,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–15249 Filed 6–9–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–182–AD; Amendment

39–10578; AD 98–12–24]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 Series Airplanes Equipped With

General Electric Model CF6–80A3

Series Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Airbus Model

A310 series airplanes. This action

requires a one-time inspection to detect
Federal Register / Vol. 63, No. 111 /Wednesday, June 10, 1998 /Rules and Regulations 31615

cracked or broken links of the aft engine

mounts, and replacement of any cracked

or broken link with a serviceable link.

This amendment is prompted by

issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified in this AD are

intended to detect and correct cracking

of the links of the aft engine mounts,

which could result in failure of the aft

engine attachment and consequent

separation of the engine from the

airplane.

DATES: Effective June 25, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 25,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

July 10, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

182–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from Airbus

Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

This information may be examined 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.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: The

Direction Ge ́ne ́rale de l’Aviation Civile

(DGAC), which is the airworthiness

authority for France, notified the FAA

that an unsafe condition may exist on

certain Airbus Model A310 series

airplanes. The DGAC advises that,

during a routine maintenance

inspection of a General Electric Model

CF6–80A3 series engine for an Airbus

Model A310 series airplane, a crack was

discovered on the left-hand link of the

aft engine mount assembly. The crack

measured 10 mm in length and was

located at the upper end of the link, at

the gearing location. The cause of the

crack is still under investigation. This

condition, if not corrected, could result

in failure of the aft engine attachment

and consequent separation of the engine

from the airplane.

Explanation of Relevant Service

Information

Airbus has issued All Operators Telex

(AOT) 71 06, dated October 21, 1997,

which describes procedures for a onetime detailed visual inspection to detect

cracked or broken links of the aft engine

mounts, and replacement of any cracked

or broken link with a serviceable link.

The DGAC classified this AOT as

mandatory and issued French

telegraphic airworthiness directive T97–

324–234(B), dated October 22, 1997, and

airworthiness directive 97–324–234(B),

dated November 5, 1997; in order to

assure the continued airworthiness of

these airplanes in France.

FAA’s Conclusions

This airplane model is manufactured

in France and is type certificated for

operation in the United States under the

provisions of section 21.29 of the

Federal Aviation Regulations (14 CFR

21.29) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the DGAC has kept the FAA informed

of the situation described above. The

FAA has examined the findings of the

DGAC, 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 Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, this AD is being issued to detect

and correct cracking of the links of the

aft engine mounts, which could result in

failure of the aft engine attachment and

consequent separation of the engine

from the aiplane. This AD requires

accomplishment of the actions specified

in the AOT described previously. This

AD also requires that operators report

results of inspection findings (positive

and negative) to Airbus.

Interim Action

This is considered to be interim

action until final action is identified, at

which time the FAA may consider

further rulemaking.

Determination of Rule’s Effective Date

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this 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

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the 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 that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 98–NM–182–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an
31616 Federal Register / Vol. 63, No. 111 /Wednesday, June 10, 1998 /Rules and Regulations

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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:

98–12–24 Airbus Industrie: Amendment

39–10578. Docket 98–NM–182–AD.

Applicability: Model A310 series airplanes,

equipped with General Electric Model CF6–

80A3 series engines; 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 detect and correct cracking of the links

of the aft engine mounts, which could result

in failure of the aft engine attachment and

consequent separation of the engine from the

airplane, accomplish the following:

(a) Within 5 days after the effective date of

this AD, perform a one-time detailed visual

inspection to detect cracked or broken links

of the aft engine mounts, in accordance with

Airbus All Operators Telex (AOT) 71 06,

dated October 21, 1997. If any cracked or

broken link is detected, prior to further flight,

replace the cracked or broken link with a

serviceable link, in accordance with the

AOT.

(b) Within 10 days after the effective date

of this AD, submit a report of the inspection

results (positive and negative) to Airbus

Industrie, 1 Rond Point Maurice Bellonte,

31707 Blagnac Cedex, France. Information

collection requirements contained in this

regulation have been approved by the Office

of Management and Budget (OMB) under the

provisions of the Paperwork Reduction Act of

1980 (44 U.S.C. 3501 et seq.) and have been

assigned OMB Control Number 2120–0056.

(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,

International Branch, ANM–116, 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, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(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 Airbus All Operators Telex 71 06, dated

October 21, 1997. 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 Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. 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 3: The subject of this AD is addressed

in French telegraphic airworthiness directive

T97–324–234(B), dated October 22, 1997, and

airworthiness directive 97–324–234(B), dated

November 5, 1997.

(f) This amendment becomes effective on

June 25, 1998.

Issued in Renton, Washington, on June 3,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–15250 Filed 6–9–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–SW–04–AD; Amendment

39–10583; AD 98–12–29]

RIN 2120–AA64

Airworthiness Directives; Lucas Air

Equipment Electric Hoists

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Lucas Air Equipment

electric hoists (hoists) installed on, but

not limited to, all models of Eurocopter

France SA–360 and SA–365 helicopters

that requires visually inspecting the

cable for damage before the next hoist

operation, blanking (plugging) the

electronic control box upper vent, and

performing an end-of-travel procedure

before each hoist operation. This

amendment is prompted by several

incidents of cable failures caused by

dynamic overload on the winding-up

limit due to uncontrolled excessive

speed of the cable, which is normally

regulated by the automatic speedreducing mechanism or the operator.

The actions specified by this AD are

intended to prevent breaking of the

cable, which could become entangled

with a main rotor or tail rotor blade, and

result in damage or separation of a rotor

blade, and subsequent loss of control of

the helicopter.

EFFECTIVE DATE: July 15, 1998.

FOR FURTHER INFORMATION CONTACT: Mr.

Carroll Wright, Aerospace Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Standards Staff, 2601 Meacham Blvd.,

Fort Worth, Texas 76137, phone (817)

222–5120, fax (817) 222–5961.

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 Lucas Air

Equipment hoists installed on, but not

limited to, all models of Eurocopter

France SA–360 and SA–365 helicopters

was published in the Federal Register

on April 10, 1998 (63 FR 17738). That

action proposed to require visually

inspecting the cable for damage before

the next hoist operation, plugging the

electronic control box upper vent, and

performing an end-of-travel procedure

before each hoist operation.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No