This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

29267

Vol. 61, No. 112

Monday, June 10, 1996

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93–NM–133–AD; Amendment

39–9658; AD 96–12–15]

RIN 2120–AA64

Airworthiness Directives; Airbus

Industrie Model A300, A310, and A300–

600 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A300, A310, and A300–600 series

airplanes, that requires inspections to

detect missing fasteners, cracked fitting

angles, and elongated fastener holes in

certain frames, and correction of

discrepancies. It also provides an

optional terminating action. This

amendment is prompted by

discrepancies found at the fitting angles

on the frame at which a certain

electronic rack is attached. The actions

specified by this AD are intended to

prevent damage propagation that could

lead to failure of the rack-to-structure

attachment points, and subsequently

could result in loss of airplane systems,

structural damage, and possible

electrical arcing.

DATES: Effective July 15, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 15,

1996.

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: Tim

Backman, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2797; fax (206) 227–1149.

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 A300, A310, and A300–600

series airplanes was published in the

Federal Register as a supplemental

notice of proposed rulemaking on

February 12, 1996 (61 FR 5326). That

action proposed to require inspections

to detect missing fasteners, cracked

fitting angles, and elongated fastener

holes in certain frames, and correction

of discrepancies. It also proposed to

provide an optional terminating action.

Discussion of Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 78 Airbus

Model A300, A310, and A300–600

series airplanes of U.S. registry will be

affected by this AD, that it will take

approximately 1.5 work hours per

airplane to accomplish the required

inspections, at an average labor rate of

$60 per work hour. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be $7,020,

or $90 per airplane, per inspection.

The 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.

Should an operator elect to

accomplish the optional terminating

action that is provided by this AD

action, rather than continue the

repetitive inspections, it will take

approximately 7 work hours to

accomplish it, at an average labor rate of

$60 per work hour. The cost of required

parts will be approximately $1,615 per

airplane. Based on these figures, the cost

impact of the optional terminating

action will be $2,035 per airplane.

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:
29268 Federal Register / Vol. 61, No. 112 / Monday, June 10, 1996 / Rules and Regulations

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

96–12–15 Airbus Industrie: Amendment

39–9658. Docket 93–NM–133–AD.

Applicability: Model A300 series airplanes

listed in Airbus Service Bulletin A300–53–

0300, dated October 28, 1993; Model A310

series airplanes listed in Airbus Service

Bulletin A310–53–2077, dated October 28,

1993; and Model A300–600 series airplanes

listed in Airbus Service Bulletin A300–53–

6055, dated October 28, 1993; on which

Airbus Modification No. 10414 or production

equivalent 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

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 (g) 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 failure of the electric rack-tostructure attachment points, which could

subsequently result in loss of airplane

systems, structural damage, and possible

electrical arcing, accomplish the following:

(a) Prior to the accumulation of 7,000 total

flight cycles, or within 50 flight cycles after

the effective date of this AD, whichever

occurs later, perform a detailed visual

inspection of the right-and left-hand lower

attachments of electric rack 101VU,

including the crossbeams at frames 15A and

16, to detect missing fasteners, cracked fitting

angles, or elongated fastener holes, in

accordance with Airbus Service Bulletin

A300–53–0300 (for Model A300 series

airplanes), dated October 28, 1993; Airbus

Service Bulletin A310–53–2077 (for Model

A310 series airplanes), dated October 28,

1993; or Airbus Service Bulletin A300–53–

6055 (for Model A300–600 series airplanes),

dated October 28, 1993; as applicable.

Note 2: Inspections accomplished in

accordance with Airbus Industrie All

Operator Telex (AOT) 53–03, Revision 3,

dated December 23, 1992, prior to the

effective date of this AD, are considered

acceptable for compliance with the

inspection requirements of this paragraph.

(b) If no discrepancies are identified during

the inspection required by paragraph (a) of

this AD, repeat the detailed visual inspection

thereafter at intervals not to exceed 2,300

flight cycles.

(c) If any fastener is missing or is found to

be damaged during any inspection required

by this AD, prior to further flight, replace the

fastener in accordance with Airbus Service

Bulletin A300–53–0300 (for Model A300

series airplanes), dated October 28, 1993;

Airbus Service Bulletin A310–53–2077 (for

Model A310 series airplanes), dated October

28, 1993; or Airbus Service Bulletin A300–

53–6055 (for Model A300–600 series

airplanes), dated October 28, 1993; as

applicable.

(d) If any fitting angle is found to be

cracked during any inspection required by

this AD, prior to further flight, install

Modification No. 10414 in accordance with

Airbus Service Bulletin A300–53–0294 (for

Model A300 series airplanes), dated May 17,

1993; Airbus Service Bulletin A310–53–2076

(for Model A310 series airplanes), dated May

17, 1993; or Airbus Service Bulletin A300–

53–6046 (for Model A300–600 series

airplanes), dated May 17, 1993; as applicable.

Installation of this modification constitutes

terminating action for the inspections

required by this AD.

(e) If any crossbeam is found damaged

during any inspection required by this AD,

prior to further flight, repair it in accordance

with a method approved by the Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate.

(f) Installation of Modification No. 10414

in accordance with Airbus Service Bulletin

A300–53–0294 (for Model A300 series

airplanes), dated May 17, 1993; Airbus

Service Bulletin A310–53–2076 (for Model

A310 series airplanes), dated May 17, 1993;

or Airbus Service Bulletin A300–53–6046

(for Model A300–600 series airplanes), dated

May 17, 1993; as applicable; constitutes

terminating action for the inspections

required by this AD.

(g) 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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(h) 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. (i) The inspections and

replacement shall be done in accordance

with Airbus Service Bulletin A300–53–0300,

dated October 28, 1993; Airbus Service

Bulletin A310–53–2077, dated October 28,

1993; or Airbus Service Bulletin A300–53–

6055, dated October 28, 1993; as applicable.

The modification shall be done in accordance

with the following Airbus service bulletins,

which contain the specified effective pages:

Service bulletin referenced and date Page No. Revision level

shown on page

Date shown on

page

A300–53–0294, May 17, 1993 .......................................................................... 1–34, .................................. Original ............. May 17, 1993.

A310–53–2076, May 17, 1993 .......................................................................... 1–34 ................................... Original ............. May 17, 1993.

A300–53–6046, Revision 1, Apr. 5, 1994 ......................................................... 1, 4, 11, 14–18, 21, 22,

25–31.

1 ....................... Apr. 5, 1994

2, 3, 5–10, 12, 13, 19, 20,

23, 24, 32.

Original ............. May 17, 1993.
Federal Register / Vol. 61, No. 112 / Monday, June 10, 1996 / Rules and Regulations 29269

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.

(j) This amendment becomes effective on

July 15, 1996.

Issued in Renton, Washington, on May 31,

1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–14230 Filed 6–7–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–43–AD; Amendment

39–9660; AD 96–12–17]

RIN 2120–AA64

Airworthiness Directives; Beech

(Raytheon) Model BAe 125 Series 800A

and 1000A, and Model Hawker 800 and

1000 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Beech (Raytheon)

Model BAe 125 series 800A and 1000A,

and Model Hawker 800 and 1000

airplanes, that requires an inspection to

determine if the diode soldered

connections are clean and functionally

sound. This amendment also requires

remake of the soldered connection and

replacement of the diode with a new

diode, if necessary. This amendment is

prompted by reports of imperfect

soldered connections in the engine

starting and battery emergency control

circuit. The actions specified by this AD

are intended to prevent incorrect fault

displays in the cockpit and intermittent

fault symptoms in the engine starting

and battery emergency control circuits,

as a result of imperfect soldered

connections.

DATES: Effective July 15, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 15,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Raytheon Aircraft Company,

Manager Service Engineering, Hawker

Customer Support Department, P.O. Box

85, Wichita, Kansas 67201–0085. 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,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2797; fax (206) 227–1149.

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 Beech

(Raytheon) Model BAe 125 series 800A

and 1000A, and Model Hawker 800 and

1000 airplanes was published in the

Federal Register on September 15, 1995

(60 FR 47903). That action proposed to

require an inspection to determine if the

diode soldered connections are clean

and functionally sound. That action also

proposed to require remake of the

soldered connection or replacement of

the diode with a new diode, if

necessary.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Requests to Revise the Applicability of

the AD

Two commenters request that the

applicability of the proposed rule be

revised to include all the airplane serial

numbers listed in Hawker Service

Bulletin SB 24–317, and that the letter

‘‘A’’ (i.e., U.S.-type certificated)

designation for Model BAe 125 series

800 and 1000 airplanes be deleted. One

of these commenters states that the

effectivity listing contained in Hawker

Service Bulletin SB 24–317 (which was

referenced in the proposal as the

appropriate source of service

information) does not specify either the

model suffix ‘‘A’’ or the model suffix

‘‘B’’ (i.e., CAA type certificated) for any

of the affected airplanes.

Therefore, the commenter points out

that the effectivity listing of the service

bulletin covers the worldwide fleet, not

just U.S.-registered airplanes.

The other commenter, the Civil

Aviation Authority (CAA), which is the

airworthiness authority for the United

Kingdom, also asserts that the

applicability of the proposal is incorrect

since it does not cover the worldwide

fleet. This commenter adds that, as of

August 1, 1995, the type certificate (TC)

responsibilities for Model BAe 125

series 800 and 1000, and Model Hawker

800 and 1000 airplanes have been

transferred from the CAA to the FAA.

This commenter adds that it is

important to note that, since this

transfer, AD’s issued by the FAA must

cover all of these airplane models, as

appropriate, and not just those on the

U.S. Register.

This commenter also notes that the

proposed applicability would result in

confusion among operators and will not

fulfill the obligation of the FAA with the

International Civil Aviation

Organization (ICAO). This commenter

asserts that the current Type Certificate

Data Sheet (TCDS), A3EU (Revision 24,

dated August 1, 1995), indicates that the

FAA accepted the responsibility for the

promulgation of all airworthiness

information relevant to the subject

airplanes in accordance with ICAO

Annex 8. The commenter contends that,

since the FAA is now responsible for

the continued airworthiness of all

airplanes listed in TCDS A3EU (which

includes Model BAe 125 series 800A,

800B, 1000A, and 1000B, and Model

Hawker 800 and 1000 airplanes), the

applicability of the proposal should

include all of the Model BAe 125 series

800 and 1000 airplanes, not just those

airplanes having a letter designation of

‘‘A.’’

The FAA does not agree with the

commenters’ specific request to revise

the applicability of the final rule, but

recognizes that some clarification is

necessary. The airplane models that are

the subject of this AD were originally

designed and manufactured in the

United Kingdom. The CAA issued Type

and Airworthiness Certificates for these

affected airplanes. Therefore, under

ICAO Annex 8, the United Kingdom

was the State of Design and had the

responsibility for providing other states

with continuing airworthiness

information regarding these models.

However, as of August 1, 1995, the

responsibility of design, continued

airworthiness, design data, and

manufacturing (i.e., TC responsibilities)

for all Model DH/HS/BH/BAe 125 and

Model Hawker 800 and 1000 airplanes,

has been transferred from Raytheon

Corporate Jets, Inc., Hatfield, United

Kingdom, to Beech Aircraft Corporation

(Raytheon), Wichita, Kansas, U.S.A. As

a result of this transfer, Revision 24 of

TCDS A3EU was issued, as discussed by

one of the commenters.

The FAA has reexamined TCDS A3EU

and finds that the text of the TCDS

correctly reflects U.S. type-certificated

airplanes (i.e., models having the letter