Federal Register / Vol. 62, No. 19 / Wednesday, January 29, 1997 / Proposed Rules 4217

series airplanes on which an inspection

required by paragraph (e) of this AD was

accomplished using an X-ray technique:

Inspect at intervals not to exceed 2,300

landings.

(8) For the aft passenger/crew door

structure on which an inspection required by

paragraph (e) of this AD was accomplished

using a Roto test technique: Inspect at

intervals not to exceed 8,000 landings.

(9) For the aft passenger/crew door

structure on which an inspection required by

paragraph (e) of this AD was accomplished

using an X-ray technique: Inspect at intervals

not to exceed 3,500 landings.

(10) For the areas around the fasteners in

the vicinity of stringer 12 on the aft

passenger/crew door structure on which an

inspection required by paragraph (e) of this

AD was accomplished using a visual

technique: Inspect at intervals not to exceed

6,900 landings.

(g) Prior to the accumulation of 20,000 total

landings, or within 1 year after the effective

date of this AD, whichever occurs later:

Modify the passenger/crew door structures in

accordance with Airbus Service Bulletin

A300–53–192, Revision 7, dated July 13,

1992. Accomplishment of this modification

constitutes terminating action for the

repetitive inspections required by paragraph

(f) of this AD.

(h) 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.

(i) 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

23, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–2220 Filed 1–28–97; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 96–SW–30–AD]

Airworthiness Directives; McDonnell

Douglas Helicopter Systems Model

MD–900 Series Helicopters

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

McDonnell Douglas Helicopter Systems

(MDHS) Model MD–900 series

helicopters. This proposal would

require removing certain serialnumbered main rotor swashplate

bearings (bearings) and replacing them

with airworthy bearings. This proposal

is prompted by reports that inspections

of several helicopters revealed that the

outer bearing race had been rotating

relative to the swashplate assembly,

which was evidenced by wear marks in

the rotating swashplate. The actions

specified by the proposed AD are

intended to prevent possible heat

accumulation and resulting damage to

the bearing caused by the bearing races

rotating relative to the bearing seat,

which could result in degraded

helicopter response to pilot control

input and possible loss of control of the

helicopter.

DATES: Comments must be received by

March 31, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 96–SW–30–AD, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas 76137. Comments may be

inspected at this location between 9:00

a.m. and 3:00 p.m., Monday through

Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Mr.

Greg DiLibero, Aerospace Engineer,

FAA, Los Angeles Aircraft Certification

Office, 3960 Paramount Blvd.,

Lakewood, California 90712, telephone

(310) 627–5231, fax (310) 627–5210.

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

should 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 No. 96–SW–30–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, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

96–SW–30–AD, 2601 Meacham Blvd.,

Room 663, Fort Worth, Texas 76137.

Discussion

This document proposes the adoption

of a new AD that is applicable to MDHS

Model MD–900 series helicopters. This

proposal would require, before further

flight, inspecting the bearing, part

number (P/N) 900C3010100–101, to

determine if a bearing having a serial

number (S/N) of S/N 059150–E0019,

S/N 059150–E0020, S/N 059150–E0021,

S/N 059150–E0022, S/N 059150–E0023,

S/N 059150–E0024, S/N 059150–E0025,

S/N 059150–E0026, S/N 059150–E0027,

S/N 059150–E0028, S/N 059150–E0029,

or S/N 059150–E0030 is installed, and

if so, removing and replacing the

bearing with an airworthy bearing. This

proposal is prompted by reports of

inspections of several helicopters that

indicated the outer bearing race had

been rotating relative to the swashplate

assembly, which was evidenced by wear

marks in the rotating swashplate. An

investigation revealed that 12 nonconforming bearings had been released

to production. Some of the 12 bearings

have been located. The actions specified

by the proposed AD are intended to

prevent possible heat accumulation and

resulting damage to the bearing caused

by the bearing races rotating relative to

the bearing seat, which could result in

degraded helicopter response to pilot

control input and possible loss of

control of the helicopter.

Since an unsafe condition has been

identified that is likely to exist or

develop on other MDHS Model MD–900

series helicopters of the same type

design, the proposed AD would require,

before further flight, inspecting the

bearing, P/N 900C3010100–101, to

determine if a bearing having S/N
4218 Federal Register / Vol. 62, No. 19 / Wednesday, January 29, 1997 / Proposed Rules

059150–E0019, S/N 059150–E0020, S/N

059150–E0021, S/N 059150–E0022, S/N

059150–E0023, S/N 059150–E0024, S/N

059150–E0025, S/N 059150–E0026, S/N

059150–E0027, S/N059150–E0028, S/N

059150–E0029, or S/N 059150–E0030 is

installed; and, if installed, removing and

replacing that bearing with an airworthy

bearing.

The FAA estimates that 20 helicopters

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 1.5 work hours per

helicopter to determine the bearing’s

S/N, 12 work hours per helicopter to

remove and replace a bearing, if

necessary, and that the average labor

rate is $60 per work hour. Replacement

bearings would cost $8,765 per

helicopter, however, replacement

bearings are covered by a

manufacturer’s warranty. Based on these

figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $5,400, assuming five

helicopters will require removal and

replacement of the bearing.

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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive to

read as follows:

McDonnell Douglas Helicopter Systems:

Docket No. 96–SW–30–AD.

Applicability: Model MD–900 series

helicopters, certificated in any category.

Note 1: This AD applies to each helicopter

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

helicopters 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 (h) 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 helicopter

from the applicability of this AD.

Compliance: Required before further flight,

unless accomplished previously.

To prevent possible heat accumulation and

resulting damage to the main rotor

swashplate bearing (bearing) caused by the

bearing races rotating relative to the bearing

seat, which could result in degraded

helicopter response to pilot control input and

possible loss of control of the helicopter,

accomplish the following:

(a) Disconnect the lower end of the main

rotor pitch links. Disconnecting the drive

link may make the inspection easier.

(b) Cut the safety wire and remove the

inner and outer labyrinth seals, part number

(P/N) 900C2010194–101 and P/N

900C201190–101, respectively, and the inner

and outer bearing retaining rings.

(c) Inspect the bearing, part number (P/N)

900C3010100–101, to determine if it has one

of the following serial numbers (S/N): S/N

059150–E0019, S/N 059150–E0020, S/N

059150–E0021, S/N 059150–E0022, S/N

059150–E0023, S/N 059150–E0024, S/N

059150–E0025, S/N 059150–E0026, S/N

059150–E0027, S/N 059150–E0028, S/N

059150–E0029, or S/N 059150–E0030.

Note 2: S/N’s similar to those above were

produced without the character ‘‘E’’ in the

number. This AD is only concerned with

those that contain the character ‘‘E’’.

(d) Enter into the helicopter Log Book the

bearing S/N.

(e) If a bearing having one of the S/N’s

stated in paragraph (c) of this AD is installed

on the helicopter, remove the bearing and

replace it with an airworthy bearing prior to

further flight.

(f) Prior to the installation of a swashplate

assembly, inspect the bearing in accordance

with the requirements of this AD.

(g) Report the results of all inspections

required by this AD within 72 hours to the

Manager, Los Angeles Aircraft Certification

Office, 3960 Paramount Blvd., Lakewood,

California 90712. Reporting requirements

have been approved by the Office of

Management and Budget and assigned OMB

control number 2120–0056.

(h) 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 Aircraft Certification Office, FAA.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Los Angeles Aircraft

Certification Office.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles Aircraft

Certification Office.

Issued in Fort Worth, Texas, on January 20,

1997.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–2215 Filed 1–28–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 71

[Airspace Docket No. 97–ANM–01]

Proposed Establishment of Class D

and Class E Airspace, Redmond,

Oregon

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Notice of Proposed Rulemaking

(NPRM).

SUMMARY: This proposed rule would

establish the Redmond, Oregon, Class D

and Class E airspace areas to

accommodate the commissioning of an

Airport Traffic Control Tower (ATCT) at

Roberts Field. Additionally, this notice

proposes to redesignate the existing

Class E surface area at Roberts Field as

part-time to preclude the concurrent

existence of the different classes of

airspace designated as surface areas at

the same location. These areas would be

depicted on aeronautical charts for pilot

reference.

DATES: Comments must be received on

or before March 8, 1997.

ADDRESSES: Send comments on the

proposal in triplicate to: Manager,

Operations Branch, ANM–530, Federal

Aviation Administration, Docket No.

97–ANM–01, 1601 Lind Avenue SW.,

Renton Washington 98055–4056.

The official docket may be examined

at the same address.