11764 Federal Register / Vol. 62, No. 49 / Thursday, March 13, 1997 / Rules and Regulations

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 final rule does

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)

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 final

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, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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

(AD) to read as follows:

97–06–05 Avions Pierre Robin:

Amendment 39–9962; Docket No. 92–

CE–25–AD.

Applicability: Model R2160 airplanes (all

serial numbers), 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 (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 initially within the

next 100 hours time-in-service (TIS) after the

effective date of this AD, unless already

accomplished, and thereafter as follows, as

applicable:

1. If the width of the lower plate of the

bottom bracket of the nose landing gear leg

is 84 millimeters: at intervals not to exceed

500 hours TIS; or

2. If the width of the lower plate of the

bottom bracket of the nose landing gear leg

is less than 84 millimeters: at intervals not

to exceed 100 hours TIS.

To prevent nose landing gear failure

caused by cracks in the weld area between

the strut and the lower plate of the nose

landing gear leg, which could result in loss

of control of the airplane during landing

operations, accomplish the following:

(a) Inspect, using dye penetrant methods,

the weld area between the strut and the lower

plate of the nose landing gear leg for cracks

in accordance with Avions Pierre Robin

Service Bulletin (SB) No. 101, Revision 3,

dated March 5, 1992.

(b) If any crack is found during any

inspection required by this AD, prior to

further flight, replace the strut with a new or

serviceable strut.

(1) If the replacement strut is not new,

prior to further flight after installing the strut,

accomplish the inspection specified in

paragraph (a) of this AD.

(2) Replacing the strut with a new or

serviceable strut does not eliminate the

repetitive inspection requirement of this AD.

(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 initial or repetitive

compliance times that provides an equivalent

level of safety may be approved by the

Manager, Brussels Aircraft Certification

Division, FAA, Europe, Africa, and Middle

East Office, c/o American Embassy, B–1000

Brussels, Belgium. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Brussels Aircraft Certification Division.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Brussels Aircraft

Certification Division.

(e) The inspection required by this AD

shall be done in accordance with Avions

Pierre Robin Service Bulletin No. 101,

Revision 3, dated March 5, 1992. This

incorporation by reference was approved by

the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51. Copies may be obtained from Avions

Pierre Robin, 1, Route de Troyes, 21121

Darois France. Copies may be inspected at

the FAA, Central Region, Office of the

Assistant Chief Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri, or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment (39–9962) becomes

effective on May 16, 1997.

Issued in Kansas City, Missouri, on March

6, 1997.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 97–6256 Filed 3–12–97; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 96–CE–11–AD; Amendment 39–

9963; AD 97–06–06]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Aircraft Company (Formerly Beech

Aircraft Corporation) 90, 99, 100, 200,

and 1900 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

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

Raytheon Aircraft Company (Raytheon)

90, 99, 100, 200, and 1900 series

airplanes (formerly referred to as Beech

90, 99, 100, 200, and 1900 series

airplanes), and modifying any chair

where the locking pin fails to fully

engage or is misaligned. AD 92–27–10

resulted from reports of pilot and

copilot chair locking pin malfunctions.

Since issuance of that AD, the Federal

Aviation Administration (FAA) has

determined that additional airplanes

should be subject to the pilot and

copilot chair locking pin inspection and

possible modification, and that the

inspection should be accomplished in

accordance with revised procedures.

This AD retains the inspection and

possible modification requirements of

AD 92–27–10; incorporates additional

airplanes into the applicability over that

included in AD 92–27–10; and requires

the inspection in accordance with

revised service information. The actions

specified by this 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: Effective May 9, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 9,

1997.
Federal Register / Vol. 62, No. 49 / Thursday, March 13, 1997 / Rules and Regulations 11765

ADDRESSES: Service information that

applies to this AD may be obtained from

the Raytheon Aircraft Company, P.O.

Box 85, Wichita, Kansas 67201–0085.

This information may also be examined

at 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; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

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:

Events Leading to the Issuance of This

AD

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to include an AD that would

apply to Raytheon 90, 99, 100, 200, and

1900 series airplanes (formerly referred

to as Beech 90, 99, 100, 200, and 1900

series airplanes) was published in the

Federal Register as a notice of proposed

rulemaking (NPRM) on June 13, 1996

(61 FR 29994). The NPRM proposed to

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 the 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.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposed rule or the FAA’s

determination of the cost to the public.

The FAA’s Determination

After careful review of all available

information related to the subject

presented above, the FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial corrections. The FAA has

determined that these minor corrections

will not change the meaning of the AD

and will not add any additional burden

upon the public than was already

proposed.

Cost Impact

The FAA estimates that 4,971

airplanes in the U.S. registry will be

affected by this AD, that it will take

approximately 1 workhour per airplane

to accomplish the required 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 this 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 will take approximately 2

workhours per airplane at an average

labor rate of $60 per hour ($120 per

airplane).

Regulatory Impact

The regulations adopted herein will

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 final rule does

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)

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 final

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, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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

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:

97–06–06 Raytheon Aircraft Company

(formerly Beech Aircraft Corporation):

Amendment 39–9963; 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 Nos.

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

65–A90–1 (U–21A) ................................................................................... LM–1 through LM–63, 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.
11766 Federal Register / Vol. 62, No. 49 / Thursday, March 13, 1997 / Rules and Regulations

Models Serial Nos.

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

F90 ............................................................................................................ LA–2 through LA–236.

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.

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

assure 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 the

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 possible

modification required by paragraph (a) of this

AD is 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) The inspection required by this AD

shall be done in accordance with Beech

Service Bulletin No. 2444, Revision II, dated

May 1995. This incorporation by reference

was approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from the Raytheon Aircraft Company, P.O.

Box 85, Wichita, Kansas 67201–0085. Copies

may be inspected at the FAA, Central Region,

Office of the Assistant Chief Counsel, Room

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

Missouri, or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(f) This amendment (39–9963) supersedes

AD 92–27–10, Amendment 39–8444.

(f) This amendment (39–9963) becomes

effective on May 9, 1997.

Issued in Kansas City, Missouri, on March

5, 1997.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 97–6255 Filed 3–12–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 71

[Docket No. 97–ACE–4]

Amendment to Class E Airspace,

Wahoo, NE

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Direct final rule; request for

comments.

SUMMARY: This action amends the Class

E airspace area at Wahoo Municipal

Airport, Wahoo, NE. The Federal

Aviation Administration has developed

a Standard Instrument Approach

Procedure (SIAP) based on the Global

Positioning System (GPS) which has

made this change necessary. The effect

of this rule is to provide additional

controlled airspace for aircraft arriving