This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

25417

Vol. 61, No. 99

Tuesday, May 21, 1996

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–NM–264–AD]

RIN 2120–AA64

Airworthiness Directives; de Havilland

Model DHC–7 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 de Havilland Model DHC–7

series airplanes. This proposal would

require repetitive non-destructive

inspections to detect disbonding of

fuselage skin panels, and repair, if

necessary. This proposal is prompted by

a report of disbonding on fuselage skin

panels, which was attributed to a

manufacturing process error. The

actions specified by the proposed AD

are intended to prevent disbonding of

the skin panels of the fuselage, which

could result in degradation of the

structural capability of the airplane

fuselage.

DATES: Comments must be received by

July 1, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 95–NM–

264–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

Bombardier, Inc., Bombardier Regional

Aircraft Division, Garratt Boulevard,

Downsview, Ontario, Canada M3K 1Y5.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Sol

Maroof, Aerospace Engineer, Airframe

and Propulsion Branch, ANE–171, FAA,

New York Aircraft Certification Office,

Engine and Propeller Directorate, 10

Fifth Street, Third Floor, Valley Stream,

New York 11581; telephone (516) 256–

7522; fax (516) 568–2716.

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 above. 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

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–264–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–264–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

Transport Canada Aviation, which is

the airworthiness authority for Canada,

recently notified the FAA that an unsafe

condition may exist on certain de

Havilland Model DHC–7 series

airplanes. Transport Canada Aviation

advises that it has received a report

indicating that, during a routine

inspection, disbonding was discovered

on a fuselage skin panel. Investigation

revealed that the apparent cause of the

disbonding was due to the initial

material preparation process that was

used on the fuselage skin panels during

manufacture. Such disbonding, if not

corrected, could result in degradation of

the structural capability of the airplane

fuselage.

Explanation of Relevant Service

Information

Bombardier has issued Service

Bulletin S.B. 7–51–1, Revision ‘A’,

dated March 31, 1995, which describes

procedures for conducting repetitive

non-destructive inspections of de

Havilland Model DHC–7 series

airplanes to detect disbonding of the

fuselage skin panels. Transport Canada

Aviation classified this service bulletin

as mandatory and issued Canadian

airworthiness directive CF–94–15 in

order to assure the continued

airworthiness of these airplanes in

Canada.

FAA’s Conclusions

This airplane model is manufactured

in Canada 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,

Transport Canada Aviation has kept the

FAA informed of the situation described

above. The FAA has examined the

findings of Transport Canada Aviation,

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 the Requirements of the

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design, the proposed AD would

require repetitive non-destructive

inspections to detect disbonding of the

fuselage skin panels. These inspections

would be required to be accomplished

in accordance with the service bulletin

described previously.
25418 Federal Register / Vol. 61, No. 99 / Tuesday, May 21, 1996 / Proposed Rules

If any disbonding is detected on any

fuselage skin panel, its repair would be

required to be accomplished in

accordance with a method approved by

the FAA.

Cost Impact

The FAA estimates that 50 de

Havilland Model DHC–7 series

airplanes of U.S. registry would be

affected by this proposed AD, that it

would take approximately 18 work

hours per airplane to accomplish the

proposed inspections, 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 $54,000, or $1,080 per

airplane, per inspection cycle.

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.

Regulatory Impact

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:

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:

De Havilland, Inc: Docket 95–NM–264–AD.

Applicability: Model DHC–7 series

airplanes, serial numbers 003 through 113

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 (b) 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 disbonding of the skin panels

of the fuselage, which could result in

degradation of the structural capability of the

airplane fuselage, accomplish the following:

(a) Within 6 months after the effective date

of this AD, perform a non-destructive

inspection to detect disbonding of the

fuselage skin panels, in accordance with the

Accomplishment Instructions of Bombardier

Service Bulletin S.B. 7–51–1, Revision ’A’,

dated March 31, 1995.

(1) If no disbonding is detected, repeat the

inspection thereafter at intervals not to

exceed 3 years.

(2) If any disbonding is detected, prior to

further flight, repair it in accordance with a

method approved by the Manager, New York

Aircraft Certification Office (ACO), FAA,

Engine and Propeller Directorate.

(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, New York

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

New York ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York 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 May 14,

1996.

S. R. Miller,

Acting Manager,Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–12602 Filed 5–20–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 96–NM–54–AD]

RIN 2120–AA64

Airworthiness Directives; Beech

(Raytheon) Model Hawker 1000 and

BAe 125–1000A Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to Beech

(Raytheon) Model Hawker 1000 and

BAe 125–1000A series airplanes, that

currently requires inspections to detect

various discrepancies of the fuel hose

assemblies on the auxiliary power unit

(APU), and correction of any

discrepancy found. That AD was

prompted by several reports of heat

damage to the fuel hose assembly on the

APU. This action would add a

requirement to replace the existing

conduit of the fuel feed hose with new

improved conduit, which would

terminate the repetitive inspections. The

actions specified by the proposed AD

are intended to prevent failure of a fuel

hose due to heat damage caused by

incorrect routing or bleed air leakage;

such failure could result in a

malfunction of the APU, a fuel fire in

the fuselage rear equipment bay, and

reduced structural integrity of the

surrounding structure.

DATES: Comments must be received by

July 1, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

54–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

Beech Aircraft Corporation, Hawker

Customer Support Department, P.O. Box

85, Wichita, Kansas 67201–0085. This