Federal Register / Vol. 60, No. 98 / Monday, May 22, 1995 / Rules and Regulations 27007

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.

(e) This amendment becomes effective on

June 21, 1995.

Issued in Renton, Washington, on May 9,

1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–11907 Filed 5–19–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–146–AD; Amendment

39–9229; AD 95–10–12]

Airworthiness Directives; Airbus Model

A320–111, –211, and –212 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A320–111, –211, and –212 series

airplanes, that requires modification of

the junction box and connector

backshells of a certain electrical harness

assembly. This amendment is prompted

by a report indicating that traces of

fungus and corrosion have been found

on the electrical harness junction box of

the thrust reverser. The actions

specified by this AD are intended to

prevent such corrosion, which could

result in multiple faults in the thrust

reverser position indication, and

subsequent uncontrolled reduction of

engine power.

DATES: Effective June 21, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 21,

1995.

ADDRESSES: 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 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:

Stephen Slotte, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2797; fax (206) 227–1320.

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 Airbus

Model A320–111, –211, and –212 series

airplanes was published in the Federal

Register on December 27, 1994 (59 FR

66493). That action proposed to require

modification of the junction box and

connector backshells of the electrical

harness assembly of the thrust reverser.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the two

comments received.

Both commenters support the

proposed rule.

Since issuance of the notice, Airbus

has issued Service Bulletin A320–71–

1011, Revision 1, dated June 27, 1994.

This service bulletin is essentially

identical to the original issue, but

contains certain editoral changes. The

FAA has revised the final rule to

include reference to this revision of the

service bulletin as an alternative source

of service information.

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the change

previously described. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

The FAA estimates that 50 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 24

work hours per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Required parts will be supplied by

ROHR, Inc. (the manufacturer of the

junction box, connector backshells, and

the electrical harness assembly) at no

cost to the operators. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$72,000, or $1,440 per airplane.

The total cost impact figure discussed

above is 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.

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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

95–10–12 Airbus Industrie: Amendment

39–9229. Docket 94–NM–146–AD.

Applicability: Model A320–111, –211, and

–212 series airplanes powered by CFM 56–

5A engines equipped with an electrical

harness assembly having part number (P/N)

238W0908–513; on which Airbus

Modification 23693 (reference Airbus Service

Bulletin A320–71–1011) has not been

installed; 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 use the authority
27008 Federal Register / Vol. 60, No. 98 / Monday, May 22, 1995 / Rules and Regulations

provided in paragraph (b) 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

multiple faults in the thrust reverser position

indication, and subsequent uncontrolled

reduction of engine power, accomplish the

following:

(a) Within 3,000 flight hours after the

effective date of this AD, modify the junction

box, connector backshells, and the electrical

harness assembly of the thrust reverser, in

accordance with Airbus Service Bulletin

A320–71–1011, dated November 17, 1993, or

Revision 1, dated June 27, 1994.

(b) 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.

(c) 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.

(d) The modification shall be done in

accordance with Airbus Service Bulletin

A320–71–1011, dated November 17, 1993; or

in accordance with Airbus Service Bulletin

A320–71–1011, Revision 1, dated June 27,

1994, which contains the following list of

effective pages:

Page No.

Revision

level

shown

on page

Date shown on

page

1, 4–6 ............. 1 ........... June 27, 1994.

2, 3, 7–11 ....... Original . Nov. 17, 1993.

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.

(e) This amendment becomes effective on

June 21, 1995.

Issued in Renton, Washington, on May 9,

1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–11908 Filed 5–19–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–187–AD; Amendment

39–9233; AD 95–10–16]

Airworthiness Directives; Boeing

Model 747 Series Airplanes Equipped

with Pratt & Whitney Model JT9D

Series Engines (Excluding Model

JT9D–70 Engines)

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 747

series airplanes, that requires

modification of the nacelle strut and

wing structure, inspections and checks

to detect discrepancies, and correction

of discrepancies. This amendment is

prompted by the development of a

modification of the strut and wing

structure that improves the damage

tolerance capability and durability of

the strut-to-wing attachments, and

reduces reliance on inspections of those

attachments. The actions specified by

this AD are intended to prevent failure

of the strut and subsequent loss of the

engine.

DATES: Effective June 21, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 21,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle,

Washington 98124–2207. 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: Tim

Backman, Aerospace Engineer, Airframe

Branch, ANM–120S, FAA, Transport

Airplane Directorate, Seattle Aircraft

Certification Office, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056;

telephone (206) 227–2776; fax (206)

227–1181.

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 Boeing

Model 747 series airplanes was

published in the Federal Register on

December 21, 1994 (59 FR 65733). That

action proposed to require modification

of the nacelle strut and wing structure,

inspections and checks to detect

discrepancies in the adjacent structure,

and correction of discrepancies.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Revision of Descriptive Language

One commenter notes that the

description of the unsafe condition that

appeared in the Discussion section of

the preamble to the notice refers to ‘‘the

structural fail-safe capability of the

strut-to-wing attachment.’’ The

commenter states that this description is

inaccurate, since it implies that the

strut-to-wing attachment is inadequate.

The commenter suggests that a more

accurate description would be ‘‘damage

tolerance capability of the strut-to-wing

attachment.’’ The FAA acknowledges

that the commenter’s wording is more

accurate. The pertinent wording this

preamble to the final rule has been

revised to reflect this change.

Furthermore, the FAA considers the

new structure of the strut as meeting the

damage tolerance requirements of

amendment 45 of section 25.571,

‘‘Damage—tolerance and fatigue

evaluation of structure’’ of the Federal

Aviation Regulations (14 CFR 25.571,

amendment 45), which provides an

even higher level of safety than simply

fail-safe requirements.

One commenter provides further

information to describe the purpose of

the proposed modification of the nacelle

strut and wing structure. This

commenter suggests that the rule should

specify that the modification not only

significantly improves the load-carrying

and durability of the strut-to-wing

attachments, but ‘‘reduces the reliance

on non-routine inspections,’’ as well.

The FAA concurs with this suggestion

and has revised the Summary section of

the preamble to this final rule to include

wording relevant to this aspect.

One commenter provides clarification

of the description in the Explanation of

Service Information section of the

preamble to the proposal. That section

of the preamble described the various

terminating actions specified in the

service bulletins listed in paragraph I.C.,

Table 2, Prior or Concurrent Service