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),

37016 Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations

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: Jim

Cashdollar, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Transport Airplane Directorate, Seattle

Aircraft Certification Office, 1601 Lind

Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2785;

fax (425) 227–1181.

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 Boeing

Model 767–200 and –300 series

airplanes was published in the Federal

Register on December 29, 1999 (64 FR

72967). That action proposed to require

repetitive inspections to detect wear or

damage of the door latches and

disconnect housings in the off-wing

escape slide compartments. If wear or

damage is found, the action proposed to

require replacement of these discrepant

components with new components.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Support for the Proposed Rule

Two commenters support the

proposed rule and indicate that they are

accomplishing the requirements of this

AD on their airplanes. A third

commenter offers no comment on the

proposed rule.

Request To Revise Wording in Proposed

Rule

One commenter requests that the FAA

revise certain wording in the preamble

and body of the proposed rule. The

commenter’s suggestions and rationale

are as follows:

1. Revise statement of unsafe

condition throughout the AD to state

that the actions specified by this AD are

intended to ‘‘ensure deployment of an

escape slide during an emergency

evacuation and[,] additionally[,] in the

case of the disconnect housing, to

ensure the safety of mechanics during

maintenance.’’ The commenter states

that a broken disconnect housing could

result in unexpected inflation of an offwing slide during maintenance.

2. Revise the ‘‘Discussion’’ section of

the proposed rule to incorporate more

details about the events that prompted

this AD. Specifically, state that ‘‘Worn

or broken latches and broken disconnect

housings have also been discovered

during maintenance.’’

3. Revise the ‘‘Differences Between

Proposed Rule and Alert Service

Bulletin’’ section to reference specific

part numbers acceptable for installation.

4. Revise description of subject parts

throughout the AD from ‘‘worn and

damaged door latches and disconnect

housings of the off-wing escape slide

compartments’’ to ‘‘worn and damaged

door latches and broken disconnect

housings in the off-wing escape slide

compartments.’’ The commenter states

that, ‘‘To date, there are no reports of

‘worn’ disconnect housings, only

‘broken’ ones.’’

The FAA partially concurs with the

commenter’s requests. The FAA concurs

with the commenter’s suggested changes

to the statement of unsafe condition

described above in item 1. Accordingly,

the FAA has revised the statement of

unsafe condition in the ‘‘Summary’’

section of this final rule.

The FAA also concurs that the

commenter’s suggested changes

described above in items 2. and 3. are

accurate; however, these sections are

not restated in the final rule; thus, no

change to the final rule is necessary in

this regard.

The FAA does not concur that any

change is necessary to the description of

subject parts, as described above in item

4. The FAA considers ‘‘damage’’ of the

disconnect housings to include broken

disconnect housings. However, the FAA

does concur with the commenter’s

suggestion to revise the words ‘‘of the

off-wing escape slide compartments’’ to

‘‘in the off-wing escape slide

compartments.’’ This change has been

made throughout this final rule.

Request To Reference Forthcoming

Terminating Action

One commenter requests that the FAA

revise the proposed rule to reference a

terminating action. The commenter

states that the airplane manufacturer

will release a new service bulletin that

describes procedures for replacing

disconnect housings with new,

improved disconnect housings. The

commenter states that such replacement

is intended to eliminate the need for the

repetitive inspections of the disconnect

housings that would be required by the

proposed AD. (However, repetitive

inspections of the latches would still be

necessary.) The commenter also

suggests changes to the cost impact

information related to adding the

terminating action.

The FAA does not concur with the

commenter’s request. To date, the FAA

has not reviewed or approved the

service bulletin referenced by the

commenter. Considering the degree of

urgency associated with addressing the

subject unsafe condition, the FAA finds

that it would be inappropriate to delay

issuance of this final rule until the

service bulletin has been approved.

However, once the service bulletin and

improved parts referenced by the

commenter are available, the commenter

may request approval of an alternative

method of compliance, in accordance

with paragraph (c) of this AD. No

change to the final rule is necessary in

this regard.

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 with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

There are approximately 634 Model

767–200 and –300 series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 241 airplanes of

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

that it will take approximately 3 work

hours per airplane to accomplish the

required inspections, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of this AD on U.S. operators is estimated

to be $43,380, or $180 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 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

Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations 37017

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:

2000–11–19 Boeing: Amendment 39–11767.

Docket 98–NM–313–AD.

Applicability: Model 767–200 and –300

series airplanes, as listed in Boeing Alert

Service Bulletin 767–25A0260, dated July 9,

1998; certificated in any category; except

Model 767 series airplanes that have

undergone conversion to freighter

configurations, and on which the off-wing

escape system has been removed or

deactivated.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 as indicated, unless

accomplished previously.

To prevent non-deployment of an escape

slide during an emergency evacuation, which

could slow down the evacuation of the

airplane and result in injury to passengers or

flightcrew; and 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; accomplish the

following:

Inspections

(a) Prior to the accumulation of 6,000 total

flight hours, or within 18 months after the

effective date of this AD, whichever occurs

later, perform a detailed visual inspection to

detect wear or damage of the door latches

and disconnect housings in the off-wing

escape slide compartments, in accordance

with Boeing Alert Service Bulletin 767–

25A0260, dated July 9, 1998. Repeat the

inspection thereafter at intervals not to

exceed 6,000 flight hours or 18 months,

whichever occurs later.

Note 2: Boeing Alert Service Bulletin 767–

25A0260, dated July 9, 1998, allows

repetitive inspections of a door latch having

part number H2052–11 or H2052–115,

provided that the latch is not worn or

damaged. However, replacement of any latch

having part number H2052–11 or H2052–115

with a new latch having part number H2052–

13 is described as part of a modification of

the escape slide compartment door latching

mechanism that is specified in Boeing Alert

Service Bulletin 767–25A0174, dated August

15, 1991. Accomplishment of that

modification is required by AD 92–16–17,

amendment 39–8327, and AD 95–08–11,

amendment 39–9200. Therefore, operators

should note that any latch having part

number H2052–11 or H2052–115 found

during an inspection required by paragraph

(a) of this AD is already required to be

replaced in accordance with AD 92–16–17 or

AD 95–08–11, as applicable.

Note 3: Inspections and corrective actions

accomplished prior to the effective date of

this AD in accordance with the Validation

Copy of Boeing Alert Service Bulletin 767–

25A0260, dated April 28, 1998, are

considered acceptable for compliance with

the applicable action specified in this AD.

Replacement

(b) If any part is found to be worn or

damaged during the inspections performed in

accordance with paragraph (a) of this AD,

prior to further flight, replace the worn or

damaged part with a new part, and perform

an adjustment of the off-wing escape slide

system, in accordance with Boeing Alert

Service Bulletin 767–25A0260, dated July 9,

1998.

Alternative Methods of Compliance

(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, Seattle

Aircraft Certification Office (ACO), 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, Seattle ACO.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permits

(d) 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

(e) The actions shall be done in accordance

with Boeing Alert Service Bulletin 767–

25A0260, dated July 9, 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 Boeing

Commercial Airplane Group, P.O. Box 3707,

Seattle, Washington 98124–2207. 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.

Effective Date

(f) 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. 00–14312 Filed 6–12–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–331–AD; Amendment

39–11769; AD 2000–11–21]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A319, A320, and A321 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, A320, and A321 series airplanes,

that requires a one-time general visual

inspection to determine the part number

and serial number of the spoiler

servocontrol, and corrective action, 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 failure of the spoiler

servocontrol piston rod, which could

result in reduced 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