34562 Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations

Fokker Service Bulletin F27/28–62, dated

September 1, 1997.

(c) 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.

(d) 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.

(e) The actions shall be done in accordance

with Fokker Service Bulletin F27/28–62,

dated September 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 Fokker Services B.V.,

Technical Support Department, P.O. Box

75047, 1117 ZN Schiphol Airport, the

Netherlands. 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 Dutch airworthiness directive BLA 1997–

094 (A), dated September 30, 1997.

(f) 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. 98–16049 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–75–AD; Amendment

39–10606; AD 98–13–18]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A319 and A321–100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A319 and A321–100 series airplanes,

that requires adjustment of the landing

gear unlocked-stop screw; replacement

of the shear pins in the reduction gear

box and the landing gear pulley

assembly with new or serviceable shear

pins; a one-time inspection to detect

discrepancies of the landing gear cut-out

valve; an operational test of the uplock

mechanical control system; and followon corrective actions, if necessary. This

amendment is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by this AD are intended to

prevent non-extension of one or more

landing gears, consequent damage to the

airplane structure, and possible injury

to passengers and crewmembers.

DATES: Effective July 30, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 30,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Airbus

Model A319 and A321–100 series

airplanes was published in the Federal

Register on April 21, 1998 (63 FR

19678). That action proposed to require

adjustment of the landing gear

unlocked-stop screw; replacement of the

shear pins in the reduction gear box and

the landing gear pulley assembly with

new or serviceable shear pins; a onetime inspection to detect discrepancies

of the landing gear cut-out valve; an

operational test of the uplock

mechanical control system; and followon corrective actions, if necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the two

comments received.

The commenters support the

proposed rule.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 2 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 20 work

hours per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour. Based

on these figures, the cost impact of the

AD on U.S. operators is estimated to be

$2,400, or $1,200 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from 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.
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