Federal Register / Vol. 61, No. 106 / Friday, May 31, 1996 / Rules and Regulations 27253

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:

96–11–13 McDonnell Douglas: Amendment

39–9638. Docket 96–NM–98–AD.

Applicability: Model DC–9–81 (MD–81),

DC–9–82 (MD–82), DC–9–83 (MD–83), and

DC–9–87 (MD–87) and Model MD–88

airplanes; as listed in McDonnell Douglas

Alert Service Bulletin MD80–33A107, dated

April 25, 1996; and McDonnell Douglas Alert

Service Bulletin MD80–25A353, dated March

14, 1996; certificated in any category.

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 (d) 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 failure of the fluorescent light

ballast of the upper and lower cabin sidewall,

and subsequent failure of the dust barriers of

the outboard ceiling panel, which could

result in a fire in the passenger compartment,

accomplish the following:

(a) For all airplanes: Within 90 days after

the effective date of this AD, perform a onetime visual inspection to determine the type

of fluorescent light ballasts installed in the

upper and lower cabin sidewall, in

accordance with McDonnell Douglas Alert

Service Bulletin MD80–33A107, dated April

25, 1996.

(1) If any Bruce Industries Incorporated

ballast is installed (specified as Condition 1

in the alert service bulletin), no further action

is required by this paragraph for that ballast.

(2) If any Day-Ray Products Incorporated

ballast is installed (specified as Condition 2

in the alert service bulletin), prior to further

flight, accomplish either paragraph (a)(2)(i),

(a)(2)(ii), or (a)(2)(iii) of this AD.

(i) Install a protective cover on the ballast

in accordance with Condition 2, Option 1, of

the alert service bulletin. Or

(ii) Replace it with a Bruce Industries

Incorporated ballast, in accordance with

Condition 2, Option 2, of the alert service

bulletin. Or

(iii) Remove or disconnect it electrically,

stow it, and protect the loose wiring.

(b) For airplanes having manufacturer’s

fuselage numbers listed in McDonnell

Douglas Alert Service Bulletin MD80–

25A353, dated March 14, 1996: Within 90

days after the effective date of this AD,

remove the dust barriers from the outboard

ceiling panels, and install modified outboard

ceiling panels, in accordance with

McDonnell Douglas Alert Service Bulletin

MD80–25A353, dated March 14, 1996.

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

Day-Ray Products Incorporated ballast,

having any part number identified in

paragraph 1.2. of McDonnell Douglas Alert

Service Bulletin MD80–33A107, dated April

25, 1996, shall be installed on any airplane

unless that ballast has been modified in

accordance with that alert service bulletin.

(d) 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, Los

Angeles 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, Los Angeles ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(e) 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.

(f) The inspection and replacement shall be

done in accordance with McDonnell Douglas

Alert Service Bulletin MD80–33A107, dated

April 25, 1996. The removal of the dust

barriers and installations shall be done in

accordance with McDonnell Douglas Alert

Service Bulletin MD80–25A353, dated March

14, 1996. 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 McDonnell Douglas Corporation, 3855

Lakewood Boulevard, Long Beach, California

90846, Attention: Technical Publications

Business Administration, Department C1–

L51 (2–60). Copies may be inspected at the

FAA, Transport Airplane Directorate, 1601

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

the FAA, Los Angeles Aircraft Certification

Office, Transport Airplane Directorate, 3960

Paramount Boulevard, Lakewood, California;

or at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(g) This amendment becomes effective on

June 17, 1996.

Issued in Renton, Washington, on May 22,

1996.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–13495 Filed 5–30–96; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–102–AD; Amendment

39–9639; AD 96–11–14]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB 2000 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 Saab Model SAAB

2000 series airplanes. This action

requires inspections to detect cracking

of the lower rib of the rudder, and

repair, if necessary. This action also

provides for an optional terminating

action, which, if accomplished,

terminates the repetitive inspection

requirement. This amendment is

prompted by reports of fatigue cracking

of the lower rib of the rudder. The

actions specified in this AD are

intended to prevent such fatigue

cracking and subsequent failure of the

primary structure of the rudder, which

could result in reduced controllability

of the airplane.

DATES: Effective June 17, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 17,

1996.

Comments for inclusion in the Rules

Docket must be received on or before

July 30, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

102–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from SAAB
27254 Federal Register / Vol. 61, No. 106 / Friday, May 31, 1996 / Rules and Regulations

Aircraft AB, SAAB Aircraft Product

Support, S–581.88, Linko ̈ping, Sweden.

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:

Ruth E. Harder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–1721; fax (206) 227–1149.

SUPPLEMENTARY INFORMATION: The

Luftfartsverket (LFV), which is the

airworthiness authority for Sweden,

recently notified the FAA that an unsafe

condition may exist on certain Saab

Model 2000 series airplanes. The LFV

advises that it has received reports

indicating that cracking of the bottom

rib of the elevator has been detected on

two Model SAAB 2000 series airplanes.

Investigation revealed that, loose pieces

of the web were found inside the rudder

on one airplane. The cause of the

cracking has been attributed to fatigue.

Fatigue cracking and subsequent failure

of the rudder, if not detected and

corrected in a timely manner, could

result in reduced controllability of the

airplane.

Explanation of Relevant Service

Information

Saab has issued Service Bulletin

SAAB 2000–55–005, dated February 2,

1996, which describes procedures for

repetitive visual inspections to detect

cracking of the lower rib of the rudder.

The service bulletin also describes

procedures for a temporary repair of

cracking that is within certain specified

limits. The LFV classified this service

bulletin as mandatory and issued

Swedish airworthiness directive SAD

No. 1–088–R1 in order to assure the

continued airworthiness of these

airplanes in Sweden.

Additionally, Saab has issued Service

Bulletin 2000–55–006, dated April 23,

1996, which describes procedures to

modify the elevator by reinforcing the

lower rib. This modification

(Modification No. 5736) will prevent

failure of the rudder due to fatigue

cracking of the lower rib.

Accomplishment of the modification

eliminates the need for the repetitive

visual inspections. The LFV has

approved the technical content of this

service bulletin.

FAA’s Conclusions

This airplane model is manufactured

in Sweden and is 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 LFV has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the LFV,

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 fatigue cracking of the lower rib

of the rudder and subsequent failure of

the primary structure of the rudder.

Such failure could result in reduced

controllability of the airplane. This AD

requires repetitive visual inspections to

detect cracking of the lower rib of the

rudder, and repair, if necessary. The

inspections and certain repairs are

required to be accomplished in

accordance with Saab Service Bulletin

2000–55–005, described previously.

Repair of any cracking detected that is

beyond the limits specified in that

service bulletin is required to be

accomplished in accordance with a

method approved by the FAA.

This AD also provides for optional

modification of the rudder, which, if

accomplished, constitutes terminating

action for the repetitive inspection

requirements of this AD. If

accomplished, the modification is

required to be accomplished in

accordance with SAAB Service Bulletin

2000–55–006.

This is considered to be interim

action. The FAA is currently

considering requiring the installation of

the rudder modification that will

constitute terminating action for the

repetitive inspections required by this

AD. However, the planned compliance

time for the installation of the

modification is sufficiently long so that

notice and public comment will be

practicable.

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 96–NM–102–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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.

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
Federal Register / Vol. 61, No. 106 / Friday, May 31, 1996 / Rules and Regulations 27255

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

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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

96–11–14 SAAB Aircraft Ab: Amendment

39–9639. Docket 96–NM–102–AD.

Applicability: Model SAAB 2000 series

airplanes; having serial numbers 004 through

039, 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

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 (f) 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 fatigue cracking of the lower rib

of the rudder and subsequent reduced

controllability of the airplane, accomplish

the following:

(a) Within 20 days after the effective date

of this AD: Perform a visual inspection to

detect cracking of the lower rib of the rudder,

in accordance with Saab Service Bulletin

2000–55–005, dated February 2, 1996.

(b) If no cracking is detected: Thereafter,

repeat the inspection required by paragraph

(a) of this AD at intervals not to exceed 400

hours time-in-service, in accordance with

Saab Service Bulletin 2000–55–005, dated

February 2, 1996.

(c) If any cracking is detected that is 25 mm

in length or less: Prior to further flight,

perform a temporary repair in accordance

with paragraph 2.C. of the Accomplishment

Instructions of Saab Service Bulletin 2000–

55–005, dated February 2, 1996. Thereafter,

repeat the inspections required by paragraph

(a) of this AD at intervals not to exceed 7

days.

(d) If any cracking is detected that is more

than 25 mm in length: Prior to further flight,

repair it in accordance with a method

approved by the Manager, Standardization

Branch, ANM–113, FAA, Transport Airplane

Directorate.

(e) Modification of the lower rib of the

rudder (Modification No. 5736), in

accordance with Saab Service Bulletin 2000–

55–006, dated April 23, 1996, constitutes

terminating action for the repetitive

inspection requirements of this AD.

(f) 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,

Standardization Branch, ANM–113.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(g) 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.

(h) The inspections and temporary repair

shall be done in accordance with Saab

Service Bulletin 2000–55–005, dated

February 2, 1996. 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 SAAB Aircraft AB, SAAB

Aircraft Product Support, S–581.88,

Linko ̈ping, Sweden. 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.

(i) This amendment becomes effective on

June 17, 1996.

Issued in Renton, Washington, on May 22,

1996.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–13496 Filed 5–30–96; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF COMMERCE

Bureau of Export Administration

15 CFR Parts 754, 758, and 762

[Docket No.960523147–01]

RIN 0694–AB44

Exports of Alaskan North Slope Crude

Oil; Establishment of License

Exception TAPS

AGENCY: Bureau of Export

Administration, Commerce

ACTION: Final rule.

SUMMARY: The Bureau of Export

Administration is amending the short

supply provisions of the Export

Administration Regulations to modify

the restrictions on exports of Alaskan

North Slope crude oil and establish

License Exception TAPS authorizing

such exports, with certain conditions.

License Exception TAPS is based on: 1)

Public Law 104–58, which allows for

the export of crude oil transported by

pipeline over right-of-way granted

pursuant to section 203 of the TransAlaska Pipeline Authorization Act

(TAPS); 2) the President’s April 28,

1996 determination that exports are in

the national interest; and 3) the

President’s direction to the Secretary of

Commerce to issue a License Exception

with conditions for export of TAPS

crude oil.

EFFECTIVE DATE: May 28, 1996.

FOR FURTHER INFORMATION CONTACT:

Bernard Kritzer, Office of Chemical and

Biological Controls and Treaty

Compliance, Bureau of Export

Administration, Department of

Commerce, Telephone: (202) 482–0894.

SUPPLEMENTARY INFORMATION:

Background

Section 7(d) of the Export

Administration Act of 1979, (50 U.S.C.

app. 2406) restricts exports of crude oil

transported over right-of-way granted

pursuant to section 203 of the TransAlaska Pipeline Authorization Act (43

U.S.C. 1652), with certain exceptions,

unless the President makes certain

findings, recommends exports to the

Congress on the basis of those findings,

and the Congress then agrees to the

recommendation by joint resolution

enacted into law. Although the Export

Administration Act (EAA) expired on

August 20, 1994, the President invoked

the International Emergency Economic

Powers Act and continued in effect, to

the extent permitted by law, the

provisions of the EAA and the EAR in

Executive Order 12924 of August 19,