Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations 34563

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 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

98–13–18 Airbus Industrie: Amendment

39–10606. Docket 98–NM–75–AD.

Applicability: Model A319 series airplanes,

manufacturer’s serial numbers 578 through

625 inclusive; and Model A321–100 series

airplanes, manufacturer’s serial numbers 385

through 620 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 non-extension of one or more

landing gears, consequent damage to the

airplane structure, and possible injury to

passengers and crewmembers, accomplish

the following:

(a) Within 400 flight hours after the

effective date of this AD, accomplish the

actions required by paragraphs (a)(1), (a)(2),

(a)(3), and (a)(4) of this AD, in accordance

with Airbus Industrie A319/A321 All

Operator Telex (AOT) 32–15, dated July 1,

1997.

(1) Adjust the landing gear unlocked-stop

screw.

(2) Replace the shear pins in the reduction

gear box and the landing gear pulley

assembly with new or serviceable shear pins.

(3) Inspect the cut-out valve for

discrepancies. If any discrepancy to the cutout valve is detected, accomplish the

requirements of paragraphs (a)(3)(i) and

(a)(3)(ii) of this AD at the time specified in

the AOT.

(i) Replace the cut-out valve with a new or

serviceable part within the time specified in

the AOT.

(ii) After replacing the cut-out valve,

perform a functional test of the normal

extension and retraction of the landing gear

and of the free-fall extension system. If any

discrepancy is detected during the

accomplishment of either of the functional

tests, prior to further flight, repair in

accordance with the AOT.

(4) Perform an operational test of the gear

uplock and door uplock mechanical control

system. If any discrepancy is detected during

the accomplishment of the operational test,

prior to further flight, repair in accordance

with the AOT.

(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,

International Branch, ANM–116, 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, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(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) The actions shall be done in accordance

with Airbus Industrie A319/A321 All

Operator Telex (AOT) 32–15, dated July 1,

1997. 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 Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Note 3: The subject of this AD is addressed

in French airworthiness directive 97–177–

101(B), dated August 13, 1997.

(e) This amendment becomes effective on

July 30, 1998.

Issued in Renton, Washington, on June 11,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–16048 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–86–AD; Amendment 39–

10599; AD 98–13–11]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Aircraft Company Model 1900D

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Raytheon Aircraft

Company (Raytheon) Model 1900D

airplanes. This action requires

modifying the airplane by incorporating

Raytheon Kit No. 129–5200–1, ‘‘Ground

Fine Switch Installation Kit’’. This

action is the result of design analysis

during certification of 5.5 degree

approach landings of the Model 1900D

airplanes. The actions specified by this

AD are intended to prevent a loose or

misrigged ground fine switch, which

could result in very hard landings

causing structural damage to the

airplane and possible passenger injury.

DATES: Effective August 3, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 3,

1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

Raytheon Aircraft Company, P. O. Box

85, Wichita, Kansas 67201–0085;

telephone: (800) 625–7043. This

information may also be examined at

the Federal Aviation Administration

(FAA), Central Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 97–CE–86–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.

Randy Griffith, Aerospace Engineer,

FAA, Wichita Aircraft Certification

Office, Room 100, 1801 Airport Rd.,

Wichita, Kansas 67209; telephone: (316)

946–4145; 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 Model 1900D
34564 Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations

airplanes was published in the Federal

Register as a notice of proposed

rulemaking (NPRM) on February 2, 1998

(63 FR 3278). The NPRM proposed to

require modifying the airplane by

incorporating Raytheon Kit No. 129–

5200–1, ‘‘Ground Fine Switch

Installation Kit’’. Accomplishment of

the proposed action as specified in the

NPRM would be in accordance with

Raytheon Aircraft Mandatory Service

Bulletin No. 2714, Issued: June, 1997.

The NPRM was the result of design

analysis during certification of 5.5

degree approach landings of the Model

1900D airplanes.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. The

comments received on the proposed

rule have been given due consideration.

The manufacturer, Raytheon Aircraft

Company, states that the ‘‘Ground Fine

Switch Installation Kit’’ number is

wrong. The kit number cited in the

NPRM was P129–5200–1. Raytheon

states that the ‘‘P’’ in front of the

number was used to indicate

‘‘prototype’’ during the approval

process. The actual kit number should

be 129–5200–1. The FAA concurs and

will remove the ‘‘P’’ on all references to

Raytheon Kit No. P129–5200–1 in the

preamble and body of the AD.

The other comment received was from

the Air Line Pilots Association (ALPA).

ALPA concurs with the actions in the

proposed AD.

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 the

corrections mentioned above and minor

editorial corrections. The FAA has

determined that these 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 271 airplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

4 workhours per airplane to accomplish

this action, and that the average labor

rate is approximately $60 an hour.

Raytheon is providing the kit and labor

at no cost to the owners/operators under

their Warranty Credit program for 12

months after the last day of the month

that the manufacturer’s service bulletin

was issued. If there were no warranty on

the parts and labor to accomplish this

action, the cost for U.S. operators is

estimated to be $65,040 or $240 per

airplane. This figure is based on the

assumption that no affected operators

have accomplished this action.

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 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive

(AD) to read as follows:

98–13–11 Raytheon Aircraft Company

(Type Certificate No. A24CE formerly

held by the Beech Aircraft Corporation):

Amendment 39–10599; Docket No. 97–

CE–86–AD.

Applicability: Model 1900D airplanes,

serial numbers UE–1 through UE–271,

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 (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 800

hours time-in-service (TIS) after the effective

date of this AD, unless already accomplished.

To prevent a loose or misrigged ground

fine switch, which could result in very hard

landings causing structural damage to the

airplane and possible passenger injury,

accomplish the following:

(a) Modify the ground idle low pitch stop

system on the airplane by incorporating

Raytheon ‘‘Ground Fine Switch Installation

Kit’’ No. 129–5200–1 in accordance with the

Accomplishment Instructions section of

Raytheon Aircraft Mandatory Service

Bulletin No. 2714, Issued: June, 1997.

(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, Wichita Aircraft

Certification Office (ACO), Room 100, 1801

Airport Rd., 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.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita Aircraft

Certification Office.

(d) The modification required by this AD

shall be done in accordance with Raytheon

Aircraft Mandatory Service Bulletin No.

2714, Issued: June, 1997. 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 Raytheon Aircraft

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

67201–0085. Copies may be inspected at the

FAA, Central Region, Office of the Regional

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.

(e) This amendment becomes effective on

August 3, 1998.

Issued in Kansas City, Missouri, on June

10, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–16166 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U