37014 Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–380–AD; Amendment

39–11768; AD 2000–11–20]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model DHC–8–100 and –300 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Bombardier Model

DHC–8–100 and –300 series airplanes,

that requires revising the Aircraft Log

Book to correct the airplane Production

Modification List; performing an

inspection to determine which bonded

skin panels on the airplane require

bonding integrity inspections (BII); and

revising the Airworthiness Limitations

List of the Approved Maintenance Plan

to include the BII requirements. This

amendment also requires, for certain

airplanes, repetitive ultrasonic bond

inspections to detect disbonding of

airplane skin panels, and repair, 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 damage to bonded

skin panels to go undetected, which

could result in failure of the bonded

skin panels, and consequent loss of

controllability of the airplane.

DATES: Effective July 18, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 18,

2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Bombardier, Inc., Bombardier

Regional Aircraft Division, 123 Garratt

Boulevard, Downsview, Ontario M3K

1Y5, Canada. 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 FAA, Engine and

Propeller Directorate, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York;

or at the Office of the Federal Register,

800 North Capitol Street, NW., suite

700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Franco Pieri, Aerospace Engineer,

Airframe and Propulsion Branch, ANE–

171, FAA, Engine and Propeller

Directorate, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York

11581; telephone (516) 256–7526; fax

(516) 568–2716.

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 Bombardier

Model DHC–8–100 and –300 series

airplanes was published in the Federal

Register on March 31, 2000 (65 FR

17206). That action proposed to require

revising the Aircraft Log Book to correct

the airplane Production Modification

List; performing an inspection to

determine which bonded skin panels on

the airplane require bonding integrity

inspections (BII); and revising the

Airworthiness Limitations List of the

Approved Maintenance Plan to include

the BII requirements. That action also

proposed to require, for certain

airplanes, repetitive ultrasonic bond

inspections to detect disbonding of

airplane skin panels, and repair, 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 41 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 1

work hour per airplane to accomplish

the required revisions to the Aircraft

Log Book, Approved Maintenance Plan,

and inspection, and that the average

labor rate is $60 per work hour. Based

on these figures, the cost impact of the

actions required by this AD on U.S.

operators is estimated to be $2,460, or

$60 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 a substantial direct effect 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, it is determined that this

final rule does not have federalism

implications under Executive Order

13132.

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:

2000–11–20 Bombardier Inc. (Formerly de

Havilland, Inc.): Amendment 39–11768.

Docket 98–NM–380–AD.

Applicability: Model DHC–8–100 and –300

series airplanes, serial numbers 215 through

341 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

Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations 37015

alternative method of compliance in

accordance with paragraph (e) 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 damage to bonded skin panels

to go undetected, which could result in

failure of the bonded skin panels, and

consequent loss of controllability of the

airplane, accomplish the following:

Revision to Aircraft Log Book and

Airworthiness Limitations List

(a) Within 30 days after the effective date

of this AD, perform the actions required by

paragraphs (a)(1), (a)(2), and (a)(3) of this AD.

(1) Revise the Aircraft Log Book to correct

the airplane Production Modification List in

accordance with the Accomplishment

Instructions in Part A of Section III of

Bombardier Service Bulletin S.B. 8–51–2,

Revision ‘A,’ dated September 19, 1998.

(2) Perform an inspection to determine

which bonded skin panels on the airplane

require bonding integrity inspections (BII) in

accordance with the Accomplishment

Instructions in Part B of Section III of

Bombardier Service Bulletin S.B. 8–51–2,

Revision ‘A,’ dated September 19, 1998.

(3) Revise the Airworthiness Limitations

List of the Approved Maintenance Plan by

inserting the bonding integrity inspections

identified as de Havilland Maintenance Task

5500/01 and de Havilland Maintenance Task

5700/01 into the Airworthiness Limitations

List. Except as provided by paragraph (e) of

this AD: After the actions specified in

paragraph (a)(3) of this AD have been

accomplished, no alternative replacement

times or structural inspection intervals may

be approved for the bonded panels of the

empennage and wings specified in de

Havilland Maintenance Task 5500/01 and de

Havilland Maintenance Task 5700/01.

On-Condition Repetitive Inspections

(b) For airplanes on which the bonded skin

panels require BII’s, as determined in

paragraph (a)(2) of this AD: At the next

required maintenance visit, but no later than

12 months after the effective date of this AD,

perform an initial ultrasonic bond inspection

to detect disbonding of the skin panels, in

accordance with Part 5, sections 55–00–01

and/or 57–30–01, of Bombardier Production

Support Manual (PSM) 1–8–7A, dated

December 15, 1998 (for Model DHC–8–100

series airplanes); or Part 5, sections 55–00–

01 and 57–30–01 of Bombardier PSM 1–83–

7A, dated April 30, 1999 (for Model DHC–8–

300 series airplanes); as applicable.

Thereafter, repeat the ultrasonic inspection at

the interval specified in the applicable PSM.

On-Condition Repair

(c) Except as provided by paragraph (d) of

this AD, if any disbonding is detected during

any inspection required by paragraph (b) of

this AD, prior to further flight, repair in

accordance with Part 5, sections 55–00–01

and 57–30–01 of Bombardier PSM 1–8–7A,

dated December 15, 1998 (for Model DHC–8–

100 series airplanes); or Part 5, sections 55–

00–01 and 57–30–01 of Bombardier PSM 1–

83–7A, dated April 30, 1999 (for Model

DHC–8–300 series airplanes); as applicable.

(d) If any disbonding is detected during

any inspection required by paragraph (b) of

this AD; and the applicable service

information specifies to contact Bombardier

for appropriate action: Prior to further flight,

repair in accordance with a method approved

by the Manager, New York Aircraft

Certification Office (ACO), FAA, Engine and

Propeller Directorate. For a repair method to

be approved by the Manager, New York ACO,

as required by this paragraph, the Manager’s

approval letter must specifically reference

this AD.

Alternative Methods of Compliance

(e) 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, New York

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

New York ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

Special Flight Permits

(f) Special flight permits may be issued in

accordance with §§ 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.

Incorporation by Reference

(g) The Aircraft Log Book revision required

by paragraph (a)(1) and the inspection

required by paragraph (a)(2) of this AD shall

be done in accordance with Bombardier

Service Bulletin S.B. 8–51–2, Revision ‘A,’

dated September 19, 1998. 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

Bombardier, Inc., Bombardier Regional

Aircraft Division, 123 Garratt Boulevard,

Downsview, Ontario M3K 1Y5, Canada.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

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

FAA, Engine and Propeller Directorate, New

York Aircraft Certification Office, 10 Fifth

Street, Third Floor, Valley Stream, New York;

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 Canadian airworthiness directive CF–98–

31, dated September 1, 1998.

(h) This amendment becomes effective on

July 18, 2000.

Issued in Renton, Washington, on June 1,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14313 Filed 6–12–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–313–AD; Amendment

39–11767; AD 2000–11–19]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 767–200 and –300 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 767–

200 and –300 series airplanes, that

requires repetitive inspections to detect

wear or damage of the door latches and

disconnect housings in the off-wing

escape slide compartments, and

replacement of any discrepant

component with a new component. This

amendment is prompted by reports of

worn and damaged door latches and

disconnect housings in the off-wing

escape slide compartments. The actions

specified by this AD are intended to

ensure deployment of an escape slide

during an emergency evacuation. Nondeployment of an escape slide during an

emergency could slow down the

evacuation of the airplane and result in

injury to passengers or flightcrew. The

actions specified by this AD are also

intended to detect damaged disconnect

housings in the off-wing escape slide

compartments, which could result in

unexpected deployment of an escape

slide during maintenance, and

consequent injury to maintenance

personnel.

DATES: Effective July 18, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 18,

2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle,

Washington 98124–2207. This

information may be examined at the

Federal Aviation Administration (FAA),