29994 Federal Register / Vol. 61, No. 115 / Thursday, June 13, 1996 / Proposed Rules

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive

(AD) to read as follows:

The New Piper Aircraft, Inc.: Docket No. 95–

CE–21–AD.

Applicability: Model PA31T2 airplanes

(serial numbers 31T–8166001 through 31T–

8166062), certificated in any category, that

have a Parker Hannifin Wheel and Brake

Conversion Kit 199–111 incorporated in

accordance with Supplemental Type

Certificate (STC) SA599GL.

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 (c) 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 within the next 100

hours time-in-service after the effective date

of this AD, unless already accomplished.

To prevent the brake cylinder from chafing

against the landing gear emergency extension

air line when the gear is in the up and locked

position, which could result in damage to the

air line and subsequent loss of emergency

gear extension capability, accomplish the

following:

(a) Reroute the landing gear emergency

extension air line in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

section of Parker Hannifin Service Bulletin

SB7034, Revision B, dated December 19,

1995.

(b) 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.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Chicago Aircraft

Certification Office (ACO), FAA, 2300 East

Devon Avenue, Des Plaines, Illinois 60018.

The request shall be forwarded through an

appropriate FAA Maintenance Inspector,

who may add comments and then send it to

the Manager, Chicago ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Chicago ACO.

(d) All persons affected by this directive

may obtain copies of the document referred

to herein upon request to the Parker Hannifin

Corporation, Aircraft Wheel & Brake, 1160

Center Road, P.O. Box 158, Avon, Ohio

44011; or may examine this document at the

FAA, Central Region, Office of the Assistant

Chief Counsel, Room 1558, 601 E. 12th

Street, Kansas City, Missouri 64106.

Issued in Kansas City, Missouri, on June 4,

1996.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 96–14954 Filed 6–12–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 96–CE–11–AD]

RIN 2120–AA64

Airworthiness Directives; Beech

Aircraft Corporation 90, 99, 100, 200,

and 1900 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

supersede AD 92–27–10, which

currently requires inspecting the pilot

and copilot chairs to ensure that the

locking pins will fully engage in the seat

tracks on certain Beech Aircraft

Corporation (Beech) 90, 99, 100, 200,

and 1900 series airplanes, and

modifying any chair where any locking

pin fails to fully engage or is misaligned.

Reports of pilot and copilot chair

locking pin malfunctions prompted AD

92–27–10. Since issuance of that AD,

the Federal Aviation Administration

(FAA) has determined that additional

airplanes should be affected by the pilot

and copilot chair locking pins

inspection and modification (if

required), and that the inspection

should be accomplished in accordance

with revised procedures. The proposed

action would retain the inspection and

modification requirements of AD 92–

27–10; incorporate additional airplanes

into the applicability over that included

in AD 92–27–10; and require the

inspection in accordance with revised

service information. The actions

specified by the proposed AD are

intended to prevent inadvertent

movement of the pilot or copilot chair,

which could result in loss of control of

the airplane if it occurs during a critical

flight maneuver.

DATES: Comments must be received on

or before August 16, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Assistant Chief Counsel,

Attention: Rules Docket No. 96–CE–11–

AD, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106. Comments

may be inspected at this location

between 8 a.m. and 4 p.m., Monday

through Friday, holidays excepted.

Service information that applies to the

proposed AD may be obtained from the

Beech Aircraft Corporation, P.O. Box 85,

Wichita, Kansas 67201–0085. This

information also may be examined at

the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

Steve Potter, Aerospace Engineer,

Wichita Aircraft Certification Office,

FAA, 1801 Airport Road, Mid-Continent

Airport, Wichita, Kansas 67209;

telephone (316) 946–4124; facsimile

(316) 946–4407.

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 that

summarizes 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–CE–11–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, Central Region, Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 96–CE–11–AD, Room

1558, 601 E. 12th Street, Kansas City,

Missouri 64106.

Discussion

AD 92–27–10, Amendment 39–8444

(58 FR 5923, January 25, 1993),

currently requires the following on

certain Beech Aircraft Corporation

(Beech) 90, 99, 100, 200, and 1900 series
Federal Register / Vol. 61, No. 115 / Thursday, June 13, 1996 / Proposed Rules 29995

airplanes: inspecting the pilot and

copilot chairs to ensure that the locking

pins will fully engage in the seat tracks,

and modifying any chair where any

locking pin fails to fully engage or is

misaligned. Accomplishment of the

inspection required by AD 92–27–10 is

in accordance with Beech Service

Bulletin (SB) No. 2444, Revision 1,

dated September 1992.

Reports of pilot and copilot chair

locking pin malfunctions, including one

instance where the pilot chair slid back

from the full forward position,

prompted the FAA to issue AD 92–27–

10. Since issuance of that AD, the FAA

has determined that additional airplanes

should be affected by the pilot and

copilot chair locking pins inspection

and modification, and that the

inspection should be accomplished in

accordance with revised procedures.

Applicable Service Information

The Beech Aircraft Corporation has

revised SB No. 2444 to the Revision II

level (dated May 1995). The SB revision

updates airplane serial number

effectivity, and incorporates an

additional procedure to Step 5 of the

ACCOMPLISHMENT INSTRUCTIONS

section.

Evaluation of All Applicable

Information

After examining the circumstances

and reviewing all available information

related to the incidents described above,

including the referenced SB revision,

the FAA has determined that AD action

should be taken to prevent inadvertent

movement of the pilot or copilot chair,

which could result in loss of control of

the airplane if it happens during a

critical flight maneuver.

Explanation of the Provisions of the

Proposed AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other Beech 90, 99, 100, 200,

and 1900 series airplanes of the same

type design, the proposed AD would

supersede AD 92–27–10 with a new AD

that would (1) retain the requirement of

inspecting the pilot and copilot chairs to

ensure that the locking pins will fully

engage in the seat tracks, and modifying

any chair where any locking pin fails to

fully engage or is misaligned; (2)

incorporate additional airplanes into the

applicability over that included in AD

92–27–10; and (3) require the inspection

in accordance with Beech SB No. 2444,

Revision II, dated May 1995.

Cost Impact

The FAA estimates that 4,971

airplanes in the U.S. registry would be

affected by the proposed AD, that it

would take approximately 1 workhour

per airplane to accomplish the proposed

inspection, and that the average labor

rate is approximately $60 an hour. No

parts are required to accomplish the

proposed action. Based on these figures,

the total cost impact of the proposed AD

on U.S. operators is estimated to be

$298,260. This figure only takes into

account the cost of the inspection and

does not take into account the cost of

modifying any pilot or copilot seat

where the locking mechanism fails to

fully engage or is misaligned. If a pilot

or copilot seat fails to fully engage or is

misaligned, the modification would take

approximately 2 workhours per airplane

at an average labor rate of $60 per hour

($120 per airplane).

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 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) 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 has been placed 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 14

CFR part 39 of the Federal Aviation

Regulations 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

removing Airworthiness Directive (AD)

92–27–10, Amendment 39–8444 (58 FR

5923, January 25, 1993), and by adding

a new AD to read as follows:

Beech Aircraft Corporation: Docket No. 96–

CE–11–AD. Supersedes AD 92–27–10,

Amendment 39–8444.

Applicability: The following model and

serial number airplanes, certificated in any

category:

Models Serial No.

65–90, 65–A90, B90, C90, and C90A ................ LJ–1 through LJ–1307.

65–A90–1 (U–21A) ............................................. LM–1 through LM–63, LM–65, LM–67 through LM–69, LM–71 through LM–99, and LM– 112

through LM–114.

65–A90–1 (JU–21A) ........................................... LM–64, LM–66, and LM–70.

65–A90–1 (RU–21D) .......................................... LM–100, LM–102 through LM–106, and LM–116 through LM–124.

65–A90–1 (RU–21H) .......................................... LM–101 LM–107, LM–115, LM–125, LM–127, LM–128, LM–129, LM–132, LM–133, LM– 136,

LM–137, and LM–138.

65–A90–1 (RU–21A) ........................................... LM–108 through LM–111.

65–A90–1 (U–21G) ............................................. LM–126, LM–130, LM–131, LM– 134, LM–135, and LM–139 through LM–141.

65–A90–2 (RU–21B) ........................................... LS–1, LS–2, and LS–3.

65–A90–3 (RU–21C) .......................................... LT–1 and LT–2.

65–A90–4 (RU–21E) ........................................... LU–1, LU–3, LU–4, LU–7, LU–8, and LU–14.

65–A90–4 (RU–21H) .......................................... LU–2, LU–5, LU–6, LU–9, LU–10 through LU–13, and LU–15.

E90 ...................................................................... LW–1 through LW–347.

H90 (T–44A) ....................................................... LL–1 through LL–61.

F90 ...................................................................... LA–2 through LA–236.
29996 Federal Register / Vol. 61, No. 115 / Thursday, June 13, 1996 / Proposed Rules

Models Serial No.

99, 99A, A99A, B99, and C99 ............................ U–1 through U–239.

100 and A100 ..................................................... B–1 through B–94 and B–100 through B–247.

A100 (U–21F) ..................................................... B–95 through B–99.

A100–1 (U–21J) .................................................. BB–3, BB–4, and BB–5.

B100 .................................................................... BE–1 through BE–137.

200 and B200 ..................................................... BB–2 and BB–6 through BB–1440.

200C and B200C ................................................ BL–1 through BL–72 and BL–124 through BL–137.

200CT and B200CT ............................................ BN–1 through BN–4.

200T and B200T ................................................. BT–1 through BT–34.

A200 (C–12A, C–12C) ........................................ BD–1 through BD–30, and BC–1 through BC–75.

A200 (UC–12B) ................................................... BJ–1 through BJ–66.

A200CT (C–12D) ................................................ BP–1, BP–22, and BP–24 through BP–51.

A200CT(FWD–12D) ............................................ BP–7 through BP–11.

A200CT (RC–12D) .............................................. GR–1 through GR–13.

A200CT (C–12F) ................................................. BP–52 through BP–63.

A200CT (RC–12G) ............................................. FC–1, FC–2, and FC–3.

A200CT (RC–12H) .............................................. GR–14 through GR–19.

A200CT (RC–12K) .............................................. FE–1 through FE–23.

B200C (C–12F) ................................................... BL–73 through BL–112, and BL–118 through BL–123.

B200C (UC–12F) ................................................ BU–1 through BU–10.

B200C (RC–12F) ................................................ BU–11 and BU–12.

B200C (UC–12M) ............................................... BV–1 through BV–10.

B200C (RC–12M) ............................................... BV–11 and BV–12.

B200CT (FWD–12D) ........................................... FG–1 and FG–2.

B200CT (C–12F) ................................................. BP–64 through BP–71.

1900 .................................................................... UA–1, UA–2, and UA–3.

1900C .................................................................. UB–1 through UB–74, and UC–1 through UC–174.

1900C (C–12) ..................................................... UD–1 through UD–6.

1900D .................................................................. UE–1 through UE–17.

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 (d) 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 within the next 150

hours time-in-service after the effective date

of this AD, unless already accomplished.

To prevent inadvertent movement of the

pilot or copilot chair, which could result in

loss of control of the airplane if it occurs

during a critical flight maneuver, accomplish

the following:

(a) Inspect the pilot and copilot chairs to

ensure that the locking pins will fully engage

in the seat tracks in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

section of Beech Service Bulletin (SB) No.

2444, Revision II, dated May 1995. Prior to

further flight, modify any chair where any

locking pin fails to fully engage or is

misaligned in accordance with the

maintenance manual as specified in Beech

SB No. 2444, Revision II, dated May 1995.

(b) The inspection and modification

required by paragraph (a) of this AD are still

mandatory even if the actions were

previously accomplished in accordance with

Beech SB No. 2444, dated April 1992, or

Beech SB No. 2444, Revision I, dated

September 1992.

(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.

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Wichita Aircraft

Certification Office (ACO), 1801 Airport

Road, Room 100, Mid-Continent Airport,

Wichita, Kansas 67209. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Wichita ACO. Alternative methods of

compliance approved in accordance with AD

92–27–10 (superseded by this action) are not

considered approved as alternative methods

of compliance with this AD.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(e) All persons affected by this directive

may obtain copies of the document referred

to herein upon request to the Beech Aircraft

Corporation, P.O. Box 85, Wichita, Kansas

67201–0085; or may examine this document

at the FAA, Central Region, Office of the

Assistant Chief Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri 64106.

(f) This amendment supersedes AD 92–27–

10, Amendment 39–8444.

Issued in Kansas City, Missouri, on June 4,

1996.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 96–14989 Filed 6–12–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–227–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, A300–600, A310, and A320

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 certain

Airbus Model A300, A300–600, A310,

and A320 series airplanes, that currently

requires an inspection of the landing

gear brakes for wear, and replacement if

the specified wear limits are not met.

That AD also requires incorporation of

the specified wear limits into the FAAapproved maintenance inspection

program. This action would require that

certain wear limits that are dependent

on brake stack weight be used in

conjunction with specified brake stack

weights, and that maximum allowable