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
Federal Register / Vol. 63, No. 111 /Wednesday, June 10, 1998 /Rules and Regulations 31617

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 as proposed except for an

editorial change in the ‘‘Applicability’’

section of the AD where the word ‘‘and’’

has been changed to ‘‘or.’’ The FAA has

determined that this change will neither

increase the economic burden on an

operator nor increase the scope of the

AD.

The FAA estimates that 1 helicopter

of U.S. registry will be affected by this

proposed AD, that it will take

approximately 2 work hours per

helicopter to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $775. Based on

these figures, the total cost impact of the

AD on U.S. operators is estimated to be

$895 to replace the hoist and electronic

control box.

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 FAA, Office of the

Regional Counsel, Southwest Region,

2601 Meacham Blvd., Room 663, Fort

Worth, Texas 76137.

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:

AD 98–12–29 Lucas Air Equipment:

Amendment 39–10583. Docket No. 98–

SW–04–AD.

Applicability: Electric hoists, part numbers

(P/N) 76375–030, 76375–130, 76378, or

76378–100, equipped with electronic control

boxes, P/N 61148–001, 002, or 006, installed

on, but not limited to all models of

Eurocopter France SA–360 and SA–365

helicopters, certificated in any category.

Note 1: This AD applies to each electric

hoist (hoist) equipped with an electronic

control box (control box) 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 hoists 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 hoist or control box from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

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, accomplish

the following:

(a) Before the next hoist operation, visually

inspect the cable for damage in accordance

with the applicable maintenance manual,

and blank (plug) the electronic control box

upper vent with a potting compound. If the

control box has only one vent, install it with

the vent hole in the lowest position.

(b) Apply red paint to the hoist cable

starting at 0.8 meter (m) and extending to the

3m point (31.5 inches to 118 inches) from the

upper plate of the hook assembly.

Note 2: Lucas Air Equipment Service Telex

61148–25–CW–01, Revision 01, dated April

26, 1994, pertains to the subject of this AD.

(c) Thereafter, before each hoist operation,

perform the end-of-travel procedure as

follows:

(1) With approximately 3m of cable

remaining before the hook assembly reaches

the up-limit switch operating lever (upper

end of red-painted cable), reduce the cable

speed to approximately one-third of the

normal speed with the control knob. Release

the control knob to the neutral position to

stop the hook at a distance approximately

0.8m from the hoist up-limit switch operating

lever (lower end of red-painted cable).

Continue controlling the cable speed by

exclusive use of the control on the pendant,

making short and repetitive inputs until the

hook reaches a position with 5 to 10

centimeters (2 to 4 inches) between the upper

plate of the hook assembly and the up-limit

switch operating lever. After stopping the

cable at that point, place the hook against the

up-limit switch operating lever. The

procedure required by this paragraph may be

accomplished by an owner/operator (pilot)

holding at least a private pilot certificate, and

must be entered into the aircraft records

showing compliance with this paragraph in

accordance with sections 43.11 and

91.417(a)(2)(v) of the Federal Aviation

Regulations.

(2) If the hook comes fully home at an

uncontrolled speed, or the hoist exhibits

uncontrolled speed variation or absence of

automatic speed reduction, remove the hoist

assembly (hoist and control box) and replace

it with an airworthy hoist assembly before

any further hoist operation.

(d) Installation of an electronic control box,

P/N 61148–016 or P/N 61148–012, as

applicable, with installation of a hoist, P/N

76375–060, 76375–160, 76378–060, or

76378–160, is a terminating action for the

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, Rotorcraft

Standards Staff, Rotorcraft Directorate, FAA.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Rotorcraft Standards Staff.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Standards Staff.

(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

July 15, 1998.

Note 4: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

(France) AD 94–116(AB)R1, dated May 21,

1997.

Issued in Fort Worth, Texas, on June 3,

1998.

Larry M. Kelly,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 98–15443 Filed 6–9–98; 8:45 am]

BILLING CODE 4910–13–U