31608 Federal Register / Vol. 63, No. 111 /Wednesday, June 10, 1998 /Rules and Regulations

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 detect and correct cracking in the false

spar of the wing, which could result in

reduced structural integrity of the wing,

accomplish the following:

(a) Within 1,200 flight hours after the

effective date of this AD, perform a detailed

visual inspection for cracking in the false

spar of the wing, on the left and right sides

of the airplane, in accordance with CASA

Product Support Document COM 212–224,

dated November 28, 1990.

(1) If no cracking is detected, repeat the

detailed visual inspection thereafter at

intervals not to exceed 1,200 flight hours.

(2) If any cracking is detected, prior to

further flight, repair in accordance with a

method approved by either the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate; or the

Direccio ́n General de Aviacio ́n (DGAC),

which is the airworthiness authority for

Spain (or its delegated agent). Repeat the

detailed visual inspection thereafter at

intervals not to exceed 1,200 flight hours.

(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. Operators

shall submit their request 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 inspections shall be done in

accordance with CASA Product Support

Document COM 212–224, dated November

28, 1990. 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 Construcciones Aeronauticas, S.A.,

Getafe, Madrid, Spain. 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 Spanish airworthiness directive 02/96,

dated May 13, 1996.

(e) This amendment becomes effective on

July 15, 1998.

Issued in Renton, Washington, on June 3,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–15254 Filed 6–9–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–53–AD; Amendment

39–10581; AD 98–12–27]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace BAe Model ATP Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain British Aerospace

BAe Model ATP airplanes, that requires

repetitive magnetic particle inspections

to detect cracking of the splined

operating shaft of the internal door

handle on the forward passenger door,

rear passenger door, and rear baggage

door; and 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 detect and correct cracking

of the splined operating shaft of the

internal door handle, which could result

in failure of the internal door handle,

inability to operate the door during an

emergency evacuation, and consequent

injury to airplane occupants.

DATES: Effective July 15, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 15,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from AI(R) American Support, Inc.,

13850 Mclearen Road, Herndon,

Virginia 20171. 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 British

Aerospace BAe Model ATP airplanes

was published in the Federal Register

on April 9, 1998 (63 FR 17342). That

action proposed to require repetitive

magnetic particle inspections to detect

cracking of the splined operating shaft

of the internal door handle on the

forward passenger door, rear passenger

door, and rear baggage door; and

corrective actions, if necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

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 10 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 18

work hours per airplane to accomplish

the required magnetic particle

inspection, at an average labor rate of

$60 per work hour. Based on these

figures, the cost impact of the magnetic

particle inspection required by this AD

on U.S. operators is estimated to be

$10,800, or $1,080 per airplane, per

inspection cycle.

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
Federal Register / Vol. 63, No. 111 /Wednesday, June 10, 1998 /Rules and Regulations 31609

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.

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:

98–12–27 British Aerospace Regional

Aircraft [Formerly Jetstream Aircraft

Limited; British Aerospace (Commercial

Aircraft) Limited]: Amendment 39–

10581. Docket 98–NM–53–AD.

Applicability: BAe Model ATP airplanes,

constructor’s numbers 2002 through 2067

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 detect and correct cracking of the

splined operating shaft of the internal door

handle on the forward passenger door, rear

passenger door, and rear baggage door, which

could result in failure of the internal door

handle, inability to operate the door during

an emergency evacuation, and consequent

injury to airplane occupants; accomplish the

following:

(a) Prior to the accumulation of 2,000 flight

cycles on the splined operating shaft of the

internal door handle on the forward

passenger door, rear passenger door, and rear

baggage door; or within 60 days after the

effective date of this AD; whichever occurs

later: Accomplish either paragraph (a)(1) or

(a)(2) of this AD.

(1) Perform a magnetic particle inspection

to detect cracking of the splined operating

shaft of the internal door handle on the

forward passenger door, rear passenger door,

and rear baggage door, in accordance with

British Aerospace Regional Aircraft BAe ATP

Alert Service Bulletin ATP–A52–30, dated

March 19, 1997.

(i) If any crack is found, prior to further

flight, accomplish the actions required by

paragraph (a)(2).

(ii) If no crack is found, repeat the actions

required by paragraph (a) of this AD at

intervals not to exceed 1,000 flight cycles.

(2) Replace the existing splined operating

shaft with a new splined operating shaft, in

accordance with the alert service bulletin.

Repeat the actions required by paragraph (a)

of this AD within 2,000 flight cycles after the

replacement, and thereafter at intervals not to

exceed 1,000 flight cycles.

(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 request 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 British Aerospace Regional Aircraft BAe

ATP Alert Service Bulletin ATP–A52–30,

dated March 19, 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 AI(R) American Support, Inc.,

13850 Mclearen Road, Herndon, Virginia

20171. 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 British airworthiness directive 004–03–97.

(e) This amendment becomes effective on

July 15, 1998.

Issued in Renton, Washington, on June 3,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–15253 Filed 6–9–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–SW–10–AD; Amendment

39–10576; AD 98–12–22]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron Canada Model 407

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Bell Helicopter Textron

Canada (BHTC) Model 407 helicopters

that requires shimming the tail rotor

drive system bearing supports (bearing

supports). This amendment is prompted

by reports of cracked bearing hangar

support arms in the area of the fillet

radius. The actions specified by this AD

are intended to prevent failure of the

bearing supports, which could result in

excessive tail rotor drive system

vibration, loss of tail rotor drive, and

subsequent loss of control of the

helicopter.

DATES: Effective July 15, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 15,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Bell Helicopter Textron Canada,

12,800 Rue de l’Avenir, Mirabel, Quebec

JON1LO, telephone (800) 463–3036, fax

(514) 433–0272. This information may

be examined at the FAA, Office of the

Regional Counsel, Southwest Region,

2601 Meacham Blvd., Room 663, Fort

Worth, Texas; or at the Office of the

Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT: Mr.

Jurgen Priester, Aerospace Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Certification Office, 2601 Meacham