Federal Register / Vol. 60, No. 238 / Tuesday, December 12, 1995 / Proposed Rules 63665

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 USC 106(g), 40101, 40113,

44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Boeing: Docket 95–NM–98–AD.

Applicability: Model 747–400 series

airplanes powered by General Electric CF6–

80C2 or Pratt & Whitney PW4000 series

engines; as identified in Boeing Alert Service

Bulletin 747–28A2185, Revision 1, dated

September 21, 1995, and Boeing Service

Bulletin 747–28–2146, dated August 13,

1992; 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 (b) 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 fracturing of the coupling nut,

which could result in release of fuel onto the

engine cowling and a subsequent fire,

accomplish the following:

(a) Within 18 months after the effective

date of this AD, accomplish the requirements

of paragraph (a)(1) or (a)(2), as applicable.

(1) For Model 747–400 series airplanes

identified in Boeing Alert Service Bulletin

747–28A2185, Revision 1, dated September

21, 1995: Replace the strut fuel tubes and

couplings at engine numbers 1 and 4 with

new redesigned (shrouded) couplings, in

accordance with that alert service bulletin.

(2) For Model 747–400 series airplanes

having variable numbers RT641 through

RT650 inclusive, identified in Boeing Service

Bulletin 747–28–2146, dated August 13,

1992: On engine positions 1 and 4 only,

install new fuel lines, shrouded fuel line

couplings (between the strut mid bulkhead

and the wing front spar), and drain lines in

accordance with that service bulletin.

(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, Seattle

Aircraft Certification Office (ACO), 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, Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(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.

Issued in Renton, Washington, on

December 6, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–30213 Filed 12–11–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–78–AD]

Airworthiness Directives; Airbus Model

A300–600 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

certain Airbus Model A300–600 series

airplanes. This proposal would require

inspections to detect corrosion and

cracking of the lower horizontalstabilizer cutout longeron, the corner

fitting, the skin strap, and the outer

skin; and repair, if necessary. This

proposal is prompted by cracking found

at the lower corner of the horizontalstabilizer cutout longeron during a full

scale fatigue test. The actions specified

by the proposed AD are intended to

prevent such cracking, which could

result in reduced structural integrity of

the horizontal stabilizer cutout

longeron.

DATES: Comments must be received by

January 23, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 95–NM–

78–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule 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.

FOR FURTHER INFORMATION CONTACT:

Charles Huber, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 277–2589; fax (206) 227–1149.

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. 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
63666 Federal Register / Vol. 60, No. 238 / Tuesday, December 12, 1995 / Proposed Rules

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 95–NM–78–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.

95–NM–78–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

recently notified the FAA that an unsafe

condition may exist on certain Airbus

Model A300–600 series airplanes. The

DGAC advises that, during a full-scale

fatigue test, cracking was found on the

test airplane at the lower corner of the

horizontal-stabilizer cutout longeron,

between frame (FR) 87 and FR89 and

between stringer (STGR) 24 and

STGR27, left- and right-hand. The

cracking was found after 87,675

simulated flights. Such fatigue cracking,

if not corrected, could result in reduced

structural integrity of the horizontal

stablizer cutout longeron.

Airbus has issued Service Bulletin

A300–53–6042, Revision 1, dated

February 20, 1995, which describes

procedures for repetitive visual and

eddy current inspections to detect

corrosion and cracking of the lower

horizontal-stabilizer cutout longeron,

the corner fitting, the skin strap, and the

outer skin between FR87 and FR89 and

between STGR24 and STGR27, left- and

right-hand; and repair, if necessary. The

service bulletin also describes

procedures for repetitive rotating probe

inspections to detect cracks in the

fastener holes at the same locations, and

repair, if necessary. The service bulletin

also describes procedures for certain

follow-on actions, which include

installing a new corner fitting, installing

a new longeron, and performing a cold

working procedure repairing cracks of

certain measurements. The DGAC

classified this service bulletin as

mandatory and issued French

airworthiness directive (CN) 94–269–

171(B)R1, dated March 29, 1995, in

order to assure the continued

airworthiness of these airplanes in

France.

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.

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, the proposed AD would require

repetitive visual and eddy current

inspections to detect corrosion and

fatigue cracking of the lower horizontalstabilizer cutout longeron, the corner

fitting, the skin strap, and the skin

between FR87 and FR89 and between

STGR24 and STGR27, left-hand and

right-hand. The proposed AD would

also require repetitive rotating probe

inspections to detect cracks in the

fastener holes at the same locations; and

repair or certain a follow-on actions, if

necessary. The actions would be

required to be accomplished in

accordance with the service bulletin

described previously. Certain repairs

would be required to be accomplished

in accordance with a method approved

by the FAA.

Operators should note that certain

requirements of this proposed AD

would differ from actions recommended

in the referenced Airbus service

bulletin. The service bulletin specifies

that inspection thresholds and intervals

may be adjusted based on certain

average flight operations of the airplane.

However, the FAA has determined that

such adjustments would not address the

unsafe condition in a timely manner.

Therefore, this proposed AD does not

permit such adjustments. In developing

the appropriate compliance time for the

proposed rule, the FAA considered not

only the manufacturer’s

recommendation, but the safety

implications involved with cracking of

the horizontal-stabilizer cutout longeron

and the number of landings that had

been accumulated when cracking was

detected. In light of these factors, the

FAA finds the compliance times

specified in the proposed AD for

initiating the required actions to be

warranted, in that they represent an

appropriate interval of time allowable

for the affected airplanes to continue to

operate without compromising safety.

Additionally, the service bulletin

specifies that operators need not count

touch-and-go landings in determining

the total number of landings between

two consecutive inspections, even if

those landings are less than five percent

of the landings between inspection

intervals. Since the fatigue cracking that

was found in the lower horizontal

stabilizer cutout longeron is aggravated

by landing, the FAA finds that all touchand-go landings must be counted in

determining the total number of

landings between two consecutive

inspections.

The FAA estimates that 2 airplanes of

U.S. registry would be affected by this

proposed AD, that it would take

approximately 268 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 cost impact of the proposed

AD on U.S. operators is estimated to be

$32,160 to $16,080 per airplane.

The 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.

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:
Federal Register / Vol. 60, No. 238 / Tuesday, December 12, 1995 / Proposed Rules 63667

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:

Airbus Industries: Docket 95–NM–78–AD.

Applicability: Model A300–600 series

airplanes on which Airbus Modification No.

6146 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

provided in paragraph (f) 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, alternation, or

repair remove any airplane from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent reduced structural integrity of

the horizontal stabilizer cutout longeron due

to fatigue cracking, accomplish the following:

(a) Prior to the accumulation of 18,000 total

landings, or within 2,000 landings after the

effective date of this AD, whichever occurs

later: Perform a visual and an eddy current

inspection to detect cracks and/or corrosion

of Areas 1 and 2 of the lower horizontal

stabilizer cutout longeron, as defined in

Airbus Service Bulletin A300–53–6042,

Revision 1, and dated February 20, 1995.

Perform the inspections in accordance with

the service bulletin.

(b) Perform a visual and an eddy current

inspection to detect cracks and/or corrosion

of Area 3 of the lower horizontal-stabilizer

cutout longeron, as defined in Airbus Service

Bulletin A300–53–6042, Revision 1, dated

February 20, 1995. Perform these inspections

in accordance with the service bulletin, at the

later of the times specified in paragraph (b)(1)

and (b)(2) of this AD.

(1) Prior to the accumulation of 24,000

total landings, but not before the

accumulation of 18,000 total landings; or

(2) Prior to the accumulation of 2,000

landings after the effective date of this AD.

(c) If no cracking is detected during any

inspection required by this AD: Prior to

further flight, cold work and ream the

vacated fastener holes, in accordance with

Airbus Service Bulletin A300–53–6042,

Revision 1, dated February 20, 1995; and

perform the requirements of paragraph (c)(1)

or (c)(2) of this AD, as applicable.

(1) For airplanes on which no cracking is

found in Area 1 or 2: Repeat the inspections

required by paragraph (a) of this AD

thereafter at intervals not to exceed 6,000

flight cycles.

(2) For airplanes on which no cracking is

found in Area 3: Perform the various followon actions in accordance with the service

bulletin. (The follow-on actions include

installing a new corner fitting, installing a

new longeron and performing a cold working

procedure.) After accomplishment of these

follow-on actions, no further action is

required by this AD.

(d) If any cracking is detected during any

inspection required by this AD, perform the

requirements of paragraph (d)(1) or (d)(2) of

this AD, as applicable.

(1) If any cracking is found in Area 1 or 3

that is within the limits specified in Airbus

Service bulletin A300–53–6042, Revision 1,

dated February 20, 1995: Prior to further

flight, repair in accordance with the service

bulletin.

(2) If any cracking is found in Area 2, or

if any cracking is found in any area and that

cracking is beyond the limits described in

Airbus Service Bulletin A300–53–6042,

Revision 1, dated February 20, 1995: Prior to

further fight, repair in accordance with a

method approved by the Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate.

(e) If any corrosion is detected during any

inspection required by this AD, prior to

further flight, repair the corrosion in

accordance with Airbus Service Bulletin

A300–53–6042, Revision 1, dated February

20, 1995.

(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,

Standardization Branch, ANM–113.

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.

(g) 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.

Issued in Renton, Washington, on

December 6, 1995.

Darrell M. Pederson,

Acting Manger, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–30212 Filed 12–11–95; 8:45 am]

BILLING CODE 4910–13–M

FEDERAL COMMUNICATIONS

COMMISSION

47 CFR Parts 64 and 68

[CC Docket No. 87–124; FCC 95–474]

Access to Telecommunications

Equipment and Services by Persons

With Disabilities (Hearing Aid

Compatibility)

AGENCY: Federal Communications

Commission.

ACTION: Proposed rule.

SUMMARY: On November 28, 1995, the

Commission adopted a Notice of

Proposed Rulemaking (NPRM) regarding

hearing aid compatibility of wireline

telephones. Rules proposed in the

NPRM would require that all wireline

telephones in the workplace, confined

settings (e.g., hospitals, nursing homes)

and hotels and motels eventually would

be hearing aid compatible and have

volume control. This NPRM contains

proposed or modified information

collections subject to the Paperwork

Reduction Act of 1995 (PRA). It has

been submitted to the Office of

Management and Budget (OMB) for

review under Section 3507(d) of the

PRA. OMB, the general public, and

other Federal agencies are invited to

comment on the proposed or modified

information collections contained in

this proceeding.

DATES: Written comments by the public

on the NPRM and on the proposed and/

or modified information collections are

due on or before January 12, 1996, and

reply comments are due on or before

February 16, 1996. Written comments

must be submitted by the Office of

Management and Budget (OMB) on the

proposed and/or modified information

collections on or before February 12,

1996.

ADDRESSES: Office of the Secretary,

Room 222, Federal Communications

Commission, 1919 M Street, NW,

Washington, DC 20554. In addition to

filing comments with the Secretary, a

copy of any comments on the

information collections contained

herein should be submitted to Dorothy

Conway, Federal Communications

Commission, Room 234, 1919 M Street,

N.W., Washington, DC 20554, or via the

Internet to dconway@fcc.gov, and to

Timothy Fain, OMB Desk Officer, 10236

NEOB, 725—17th Street, N.W.,

Washington, DC 20503 or via the

Internet to fain—t@al.eop.gov.

FOR FURTHER INFORMATION CONTACT: Greg

Lipscomb, Attorney, 202/418–2340, Fax

202/418–2345, TTY 202/418–0484,

glipscom@fcc.gov, Network Services