Federal Register / Vol. 65, No. 16 / Tuesday, January 25, 2000 / Rules and Regulations 3799

Applicability: All Model SD3–60 SHERPA

and SD3–SHERPA series airplanes; and

Model SD3–30 series airplanes as listed in

Shorts Service Bulletin SD330–35–1, dated

February 25, 1999; 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 as indicated, unless

accomplished previously.

To prevent the loss of oxygen from the

aircraft oxygen system, accomplish the

following:

Replacement

(a) Within 24 months after the effective

date of this AD, replace oxygen system ‘‘O’’

rings, part number (P/N) MS28778, with

improved wear-resistant ‘‘O’’ rings, P/N

MS9068, in accordance with Shorts Service

Bulletins SD360 Sherpa–35–2, dated

February 25, 1999 (for Model SD3–60 Sherpa

series airplanes); SD3 Sherpa–35–3, Revision

1, dated May 5, 1999 (for Model SD3 Sherpa

series airplanes); and SD330–35–1, dated

February 25, 1999 (for Model SD3–30 series

airplanes); as applicable.

Spares

(b) As of the effective date of this AD, no

person shall install an oxygen system ‘‘O’’

ring, P/N MS28778, on any airplane.

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,

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.

Special Flight Permits

(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.

Incorporation by Reference

(e) The actions shall be done in accordance

with Shorts Service Bulletin SD3–60 Sherpa35-2, dated February 25, 1999; Shorts Service

Bulletin SD3 Sherpa-35-3, Revision 1, dated

May 5, 1999; or Shorts Service Bulletin

SD330–35–1, dated February 25, 1999; as

applicable. Shorts Service Bulletin SD3

Sherpa-35-3, Revision 1, dated May 5, 1999,

contains the following list of effective pages:

Page No. Revision level shown on page Date shown on page

1, 4, 9, 10 .............................................................................................................. 1 ............................................................ May 5, 1999.

2, 3, 5–8, 11–14 .................................................................................................... Original .................................................. February 25, 1999.

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 Short Brothers, Airworthiness &

Engineering Quality, P.O. Box 241, Airport

Road, Belfast BT3 9DZ, Northern Ireland.

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 directives 007–02–99

(for Model SD3–60 Sherpa series airplanes),

006–02–99 (for Model SD3 Sherpa series

airplanes), and 008–02–99 (for Model SD3–

30 series airplanes).

(f) This amendment becomes effective on

February 29, 2000.

Issued in Renton, Washington, on January

14, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–1502 Filed 1–24–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–09–AD; Amendment

39–11522; AD 2000–02–04]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, A300–600, and A310 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Airbus Model

A300 and all Model A300–600 and

A310 series airplanes. This action

requires performing a pitch trim system

test to detect any continuity defect in

the autotrim function, and follow-on

corrective actions, if necessary. This

amendment is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified in this AD are intended to

prevent a sudden change in pitch due to

an out-of-trim condition combined with

an autopilot disconnect, which could

result in reduced controllability of the

airplane.

DATES: Effective February 9, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February 9,

2000.

Comments for inclusion in the Rules

Docket must be received on or before

February 24, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

09–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

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 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.

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.

3800 Federal Register / Vol. 65, No. 16 / Tuesday, January 25, 2000 / Rules and Regulations

SUPPLEMENTARY INFORMATION: The

Direction Ge ́ne ́rale de l’Aviation Civile

(DGAC), which is the airworthiness

authority for France, recently notified

the FAA that an unsafe condition may

exist on certain Airbus Model A300 and

all Model A300–600 and A310 series

airplanes. The DGAC advises that an

Airbus Model A300–600 series airplane

flew with autopilot 1 (AP 1), pitch trim

1 (PT 1), and pitch trim 2 (PT 2)

engaged. When the flight crew engaged

the vertical speed mode and selected a

new vertical speed in order to change

the flight level, the vertical speed of the

airplane changed but did not remain at

the speed that had been selected by the

flight crew.

After landing, the maintenance team

performed a test with the autopilot

engaged in vertical speed mode. When

the team selected a vertical speed, the

flight director pitch bars and control

columns moved, but the pitch trim

wheels did not move. An open circuit

was found in the connection between

flight control computer 1 (FCC 1) and

flight augmentation computer 1 (FAC 1).

That connection is necessary to generate

the autotrim function.

With the autopilot engaged in

command (CMD), the FCC command

(COM) and monitor (MON) lanes send

signals to the FAC in order to ensure the

autotrim function. When the FAC does

not receive the FCC COM signal or the

FCC MON signal, the autotrim function

is inhibited, which results in an out-oftrim condition. If an autopilot

disconnect occurs when the airplane is

in an out-of-trim condition, this

condition, if not corrected, could result

in a sudden change in pitch and

consequent reduced controllability of

the airplane.

Explanation of Relevant Service

Information

Airbus has issued All Operators

Telexes (AOT) A300–22A0115 (for

Model A300 series airplanes), A300–

600–22A6042 (for Model A300–600

series airplanes), and A310–22A2053

(for Model A310 series airplanes), all

dated December 23, 1999, which

describe procedures for a pitch trim

system test to detect any continuity

defect, and follow-on corrective actions,

if necessary. Corrective actions include

repairing any discrepant wiring found

in the pitch trim system. (The AOT’s

reference Aircraft Schematic Manual

22–27–00 as an additional source of

service information for accomplishment

of the repair.) The DGAC has classified

these AOT’s as mandatory and issued

French airworthiness directive T2000–

007–301(B), dated January 4, 2000, in

order to assure the continued

airworthiness of these airplanes in

France.

FAA’s Conclusions

These airplane models are

manufactured in France and are type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the DGAC has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the DGAC,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, this AD is being issued to

prevent a sudden change in pitch due to

an out-of-trim condition combined with

an autopilot disconnect, which could

result in reduced controllability of the

airplane. This AD requires performing a

pitch trim system test to detect any

continuity defect in the autotrim

function, and follow-on corrective

actions, if necessary. The actions are

required to be accomplished in

accordance with the AOT’s described

previously.

Interim Action

This is considered to be interim

action. The manufacturer has advised

that it currently is developing additional

actions that will positively address the

unsafe condition addressed by this AD.

Once these actions are developed,

approved, and available, the FAA may

consider additional rulemaking.

Determination of Rule’s Effective Date

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this rule by

submitting such written data, views, or

arguments as they may desire.

Communications shall identify the

Rules Docket number and be submitted

in triplicate to the address specified

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–09–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, may be obtained from the

Federal Register / Vol. 65, No. 16 / Tuesday, January 25, 2000 / Rules and Regulations 3801

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:

2000–02–04 Airbus Industrie: Amendment

39–11522. Docket 2000–NM–09-AD.

Applicability: Airbus Model A300 series

airplanes, having manufacturer’s serial

number 159, 168, 188, 202, 205, 213, 299, or

302; and all Model A300–600 and A310

series airplanes; 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 as indicated, unless

accomplished previously.

To prevent a sudden change in pitch due

to an out-of-trim condition combined with an

autopilot disconnect, which could result in

reduced controllability of the airplane,

accomplish the following:

Pitch Trim System Test

(a) Within 20 days after the effective date

of this AD: Perform a pitch trim system test

to detect any continuity defect in the

autotrim function, in accordance with All

Operators Telex (AOT) A300–22A0115 (for

Model A300 series airplanes), A300–600–

22A6042 (for Model A300–600 series

airplanes), or A310–22A2053 (for Model

A310 series airplanes), all dated December

23, 1999, as applicable.

(1) If no continuity defect is found, no

further action is required by this paragraph.

Corrective Actions

(2) If any continuity defect is found, prior

to further flight, accomplish the actions

required by paragraphs (a)(2)(i) and (a)(2)(ii)

of this AD, in accordance with the applicable

AOT.

(i) Repair any discrepant wiring found in

the pitch trim system.

(ii) Repeat the initial pitch trim system test

required by paragraph (a) of this AD.

Note 2: All Operators Telexes (AOT) A300–

22A0115, A300–600–22A6042, and A310–

22A2053, all dated December 23, 1999,

reference Aircraft Schematic Manual (ASM)

22–27–00 as an additional source of service

information to accomplish the repair.

Reporting Requirement

(b) Within 10 days after accomplishing the

pitch trim system test required by this AD,

or within 10 days after the effective date of

this AD, whichever occurs later: Submit a

report of the inspection results (both positive

and negative findings) to Airbus Customer

Services, Engineering and Technical Support,

Attention Mr. Vincent Frayssinet, AI/SE–E43;

phone number 33 (0)5.62.11.04.96; Sita Code

TLSBQ7X.

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,

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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(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.

Incorporation by Reference

(e) The actions shall be done in accordance

with Airbus All Operators Telex A300–

22A0115, dated December 23, 1999; Airbus

All Operators Telex A300–600–22A6042,

dated December 23, 1999; or Airbus All

Operators Telex A310–22A2053, dated

December 23, 1999; as applicable. 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 4: The subject of this AD is addressed

in French airworthiness directive T2000–

007–301(B), dated January 4, 2000.

(f) This amendment becomes effective on

February 9, 2000.

Issued in Renton, Washington, on January

18, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–1595 Filed 1–24–00; 8:45 am]

BILLING CODE 4913–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–351–AD; Amendment

39–11521; AD 2000–02–03]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 737–300, –400, and –500 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 737–

300, –400 and –500 series airplanes, that

requires replacement, with new parts, of

the existing actuators or the rod ends on

the existing actuators at wing leading

edge slat positions 1, 2, 5, and 6. This

amendment is prompted by reports

indicating that the rod ends on several

leading edge slat actuators have

fractured. The actions specified by this

AD are intended to prevent fatigue

cracking of the rod ends of the leading

edge slat actuators, which could result

in uncommanded deployment of the

wing leading edge slat and consequent

reduced controllability of the airplane.

DATES: Effective February 29, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February

29, 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),

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.