3592 Federal Register / Vol. 60, No. 11 / Wednesday, January 18, 1995 / Proposed Rules

with McDonnell Douglas Alert Service

Bulletin A54–106, Revision 2, dated

November 3, 1994. Repeat this inspection

thereafter at intervals not to exceed 1,800

landings.

(b) If any crack(s) is found during any

inspection required by paragraph (a) of this

AD, prior to further flight, repair in

accordance with a method approved by the

Manager, Los Angeles Aircraft Certification

Office (ACO), FAA, Transport Airplane

Directorate.

(c) Accomplishment of the gap inspection

and necessary shimming in accordance with

‘‘Phase III,’’ as specified in McDonnell

Douglas Alert Service Bulletin A54–106,

Revision 2, dated November 3, 1994,

constitutes terminating action for the

inspections required by paragraph (a) of this

AD.

(d) 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, Los

Angeles 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, Los Angeles ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(e) 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 January

11, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–1134 Filed 1–17–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–220–AD]

Airworthiness Directives; Raytheon

Corporate Jets Models DH/BH/HS/BAe

125–1 to –700 Series Airplanes; BAe

125–800A Airplanes; and Hawker 800

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 Raytheon Corporate Jets Models

DH/BH/HS/BAe 125–1 to –700 series,

BAe 125–800A, and Hawker 800 series

airplanes. This proposal would require

replacement of the existing standby

static inverter with an inverter that

incorporates a circuit board assembly

sealed with a conformal coating. This

proposal is prompted by reports of

failure of the standby static inverter

caused by electrical shorting from

moisture condensing on the printed

circuit boards (PCB), due to aberrations

in the PCB conformal coating. The

actions specified by the proposed AD

are intended to prevent malfunction of

the standby static inverter due to

exposure to moisture caused by

inadequate insulation coating of the

circuit board assembly. Malfunction or

failure of the standby static inverter,

when its use is necessary, could result

in the loss of electric power for certain

equipment critical to safety of flight.

DATES: Comments must be received by

February 27, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 94–NM–

220–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

Raytheon Corporate Jets, Inc., 3 Bishops

Square, St. Albans Road West, Hatfield,

Hertfordshire, AL109NE, United

Kingdom. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2148; fax (206) 227–1320.

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 94–NM–220–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.

94–NM–220–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Civil Aviation Authority (CAA),

which is the airworthiness authority for

the United Kingdom, recently notified

the FAA that an unsafe condition may

exist on certain Raytheon Corporate Jets

Models DH/BH/HS/BAe 125–1 to -700,

BAe 125–800A, and Hawker 800 series

airplanes. The CAA advises that it has

received reports of failure of the standby

static inverter on certain of these

airplanes. Failure was caused by

electrical shorting from moisture

condensing on the printed circuit

boards (PCB), due to aberrations in the

PCB’s conformal coating. Investigation

has revealed that certain circuit boards

in the inverters have conformal coatings

that were applied improperly. The

purpose of this coating is to protect the

electric/electronic circuits from

moisture. Improper coating of the circuit

boards can allow moisture to condense

on the PCB; this could cause an

electrical short that, subsequently, could

result in a malfunction or failure of the

standby static inverter. This condition,

if not corrected, could result in the loss

of all alternating current (AC) electric

power for equipment that is critical to

safety of flight.

Raytheon Corporate Jets has issued

Hawker Service Bulletin SB.24–308–

7673A, Revision 1, dated July 11, 1994,

which describes procedures for

removing the existing standby static

inverter and replacing it with a printed

circuit board assembly that is properly

sealed with a conformal coating. The

CAA classified this service bulletin as

mandatory and issued British

airworthiness directive 005–05–94 in

order to assure the continued
Federal Register / Vol. 60, No. 11 / Wednesday, January 18, 1995 / Proposed Rules 3593

airworthiness of these airplanes in the

United Kingdom.

This airplane model is manufactured

in the United Kingdom 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 CAA has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the CAA,

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

replacement of the existing standby

static inverters with a printed circuit

board assembly that is properly sealed

with a conformal coating. The actions

would be required to be accomplished

in accordance with the service bulletin

described previously.

As a result of recent communications

with the Air Transport Association

(ATA) of America, the FAA has learned

that, in general, some operators may

misunderstand the legal effect of AD’s

on airplanes that are identified in the

applicability provision of the AD, but

that have been altered or repaired in the

area addressed by the AD. The FAA

points out that all airplanes identified in

the applicability provision of an AD are

legally subject to the AD. If an airplane

has been altered or repaired in the

affected area in such a way as to affect

compliance with the AD, the owner or

operator is required to obtain FAA

approval for an alternative method of

compliance with the AD, in accordance

with the paragraph of each AD that

provides for such approvals. A note has

been included in this notice to clarify

this requirement.

The FAA estimates that 450 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 4 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required parts

would cost approximately $410 per

airplane. Based on these figures, the

total cost impact of the proposed AD on

U.S. operators is estimated to be

$292,500, or $650 per airplane.

The total 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:

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:

Raytheon Corporate Jets, Inc. (Formerly de

Havilland; Hawker Siddeley; British

Aerospace, plc): Docket 94–NM–220–

AD.

Applicability: Model DH/BH/HS/BAe 125–

1 to –700 series airplanes, inclusive, on

which Modification 252740 has been

installed; Model BAe 125–800A series

airplanes, having constructor’s numbers prior

to number 258248; and Hawker 800 series

airplanes, 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 (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 an electrical short in the

standby static inverter due to the printed

circuit boards being exposed to condensed

moisture, accomplish the following:

(a) Within 5 months of the effective date

of this AD, remove the existing standby static

inverter (type PC 250) and replace it with a

Mod C Marathon/Flitetronics Inverter (type

PC 250), in accordance with Raytheon

Corporate Jets Hawker Service Bulletin

SB.24–308–7673A, Revision 1, dated July 11,

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.

Issued in Renton, Washington, on January

11, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–1135 Filed 1–17–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 71

[Airspace Docket No. 94–AWP–31]

Proposed Establishment of Class E

Airspace; Wahiawa Wheeler AAF, HI

AGENCY: Federal Aviation

Administration (FAA), DOT.