Federal Register / Vol. 61, No. 130 / Friday, July 5, 1996 / Rules and Regulations 35125

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This incorporation by reference of Airbus

Industrie SSID, dated September 1989, was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51, as of March 9, 1993 (58

FR 6703, February 2, 1993). The

incorporation by reference of Airbus

Industrie SSID, Revision 2, dated June 1994,

is 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.

(p) This amendment becomes

effective on August 9, 1996.

Issued in Renton, Washington, on June 17,

1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–15953 Filed 7–3–96; 8:45 am]

BILLING CODE 4910–13–U
35126 Federal Register / Vol. 61, No. 130 / Friday, July 5, 1996 / Rules and Regulations

14 CFR Part 39

[Docket No. 96–NM–128–AD; Amendment

39–9683; AD 96–14–01]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–200 (‘‘Combi’’) and 747–300

(‘‘Combi’’) Airplanes Modified in

Accordance With Heath Tecna

Supplemental Type Certificate (STC)

SA2365NM or STC SA5108NM

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 747–

200 ‘‘combi’’ and 747–300 ‘‘combi’’

airplanes. This action requires the

installation of a new hose and fitting for

the oxygen supply system. This

amendment is prompted by a report

indicating that a gasket seal in the

oxygen hose assembly was omitted

during installation. The actions

specified in this AD are intended to

prevent leakage of oxygen from the

passenger oxygen supply lines, which

could prevent an adequate flow of

oxygen from reaching passengers in the

event of a deployment of the passenger

oxygen masks.

DATES: Effective July 22, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 22,

1996.

Comments for inclusion in the Rules

Docket must be received on or before

September 3, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

128–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from Heath

Tecna Interiors, 3225 Woburn Street,

Bellingham, Washington 98226. 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: Don

Kurle, Senior Aerospace Engineer,

Systems and Equipment Branch, ANM–

130S, FAA, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington; telephone (206) 227–2798;

fax (206) 227–1181.

SUPPLEMENTARY INFORMATION: The FAA

has received a report indicating that,

due to an engineering drawing error, a

gasket seal was inadvertently omitted

from the passenger oxygen supply

assembly installed on certain Boeing

Model 747–200 and –300 ‘‘combi’’

airplanes that have been modified in

accordance with Heath Tecna

Supplemental Type Certificate (STC)

SA2365NM or STC SA5108NM.

(‘‘Combi’’ airplanes are aircraft that are

configured and certificated to transport

both cargo and passengers at the same

time on the main deck.) Without the

gasket seal, oxygen can leak from the

low pressure passenger oxygen supply

lines. This condition, if not corrected,

could prevent an adequate flow of

oxygen from reaching passengers when

the passenger oxygen masks are

deployed (due to a drop in cabin

pressure, for example). There have been

no incidents of this sort in service,

however.

Explanation of Relevant Service

Information

Heath Tecna, which is the

manufacturer of the oxygen supply

assembly, has issued Service Bulletin

H0364–35–001, dated March 15, 1996,

which describes procedures for

installing a new hose and fitting for the

oxygen system located in Zones D and

E of the airplane.

Explanation of Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design, this AD is being issued to

prevent leakage of oxygen from the

passenger oxygen supply lines, which

could prevent an adequate flow of

oxygen from reaching passengers in the

event of a deployment of the passenger

oxygen masks. This AD requires the

installation of a new hose and fitting for

the oxygen supply system. The actions

are required to be accomplished in

accordance with the service bulletin

described previously.

Cost Impact

None of the Model 747–200 ‘‘combi’’

or 747–300 ‘‘combi’’ airplanes affected

by this action are on the U.S. Register.

All airplanes included in the

applicability of this rule currently are

operated by non-U.S. operators under

foreign registry; therefore, they are not

directly affected by this AD action.

However, the FAA considers that this

rule is necessary to ensure that the

unsafe condition is addressed in the

event that any of these subject airplanes

are imported and placed on the U.S.

Register in the future.

Should an affected airplane be

imported and placed on the U.S.

Register in the future, it would require

approximately 8 work hours to

accomplish the required actions, at an

average labor charge of $60 per work

hour. Required parts would cost

approximately $400 per airplane. Based

on these figures, the cost impact of this

AD would be $880 per airplane.

Determination of Rule’s Effective Date

Since this AD action does not affect

any airplane that is currently on the

U.S. register, it has no adverse economic

impact and imposes no additional

burden on any person. Therefore, notice

and public procedures hereon are

unnecessary and the amendment may be

made effective in less than 30 days after

publication in the Federal Register.

Comments Invited

Although this action is in the form of

a final rule and was not preceded by

notice and 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–128–AD.’’ The

postcard will be date stamped and

returned to the commenter.
Federal Register / Vol. 61, No. 130 / Friday, July 5, 1996 / Rules and Regulations 35127

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.

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:

96–14–01 Boeing: Amendment 39–9683.

Docket 96–NM–128–AD.

Applicability: Model 747–200 ‘‘combi’’

airplanes and Model 747–300 ‘‘combi’’

airplanes; modified in accordance with Heath

Tecna Supplemental Type Certificate (STC)

SA2365NM or STC SA5108NM; 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 (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 leakage of oxygen from the

passenger oxygen supply lines, which could

prevent an adequate flow of oxygen from

reaching passengers in the event of a

deployment of the passenger oxygen masks,

accomplish the following:

(a) Within 15 months after the effective

date of this AD, accomplish the requirements

of paragraphs (a)(1) and (a)(2) of this AD in

accordance with Heath Tecna Service

Bulletin H0364–35–001, dated March 15,

1996:

(1) Remove the oxygen hose assembly, part

number (P/N) 173479–16; the two bushings,

P/N MS21915–12–10 and P/N AN893–19D;

the tube, P/N HPD5–74223–7; and the two

nuts, P/N AN818–12D. And

(2) Install a union-bulkhead, P/N

MS21924D10, and oxygen hose assembly, P/

N 45901–10–0200.

(b) Prior to further fight after

accomplishing the installation required by

paragraph (a)(2) of this AD, perform an

oxygen system leak test, in accordance with

Boeing 747 Maintenance Manual, Chapter

35.21.

(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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(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.

(e) The actions shall be done in accordance

with Heath Tecna Service Bulletin H0364–

35–001, dated March 15, 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 Heath

Tecna Interiors, 3225 Woburn Street,

Bellingham, Washington 98226. 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.

(f) This amendment becomes effective on

July 22, 1996.

Issued in Renton, Washington, on June 25,

1996.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–16653 Filed 7–3–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–154–AD; Amendment

39–9684; AD 96–14–02]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 767 Series Airplanes Equipped

With Pratt & Whitney Model JT9D–7R4

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 767

series airplanes, that requires a visual

inspection to verify proper clearance

between the number 18 fuel nozzle

secondary transfer fuel tube and the

pylon drain tube of the engine, and

various follow-on actions. This

amendment also requires the

installation of clamps and associated

fasteners between the environmental

control system (ECS) controller tube and

the pylon drain tube. This amendment

is prompted by reports of chafing of the

number 18 fuel nozzle secondary

transfer fuel tube of the engine due to

an improperly installed or loose pylon

drain tube. The actions specified by this

AD are intended to prevent such

chafing, which could lead to subsequent

fuel leakage and a possible engine fire.

DATES: Effective August 9, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 9,

1996.

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.

FOR FURTHER INFORMATION CONTACT:

Monica Merritt, Aerospace Engineer,

Propulsion Branch, ANM–140S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,