Federal Register / Vol. 65, No. 25 / Monday, February 7, 2000 / Rules and Regulations 5751

of flaking or corrosion; in accordance with

Raytheon Service Bulletin SB 35–3169, dated

September 1998. If any flaking or corrosion

is detected, prior to further flight, clean the

tee-piece and sleeve, and perform an oxygen

system flow check in accordance with the

service bulletin. If any discrepancy is found

during the flow check, prior to further flight,

repair the oxygen system in accordance with

the service bulletin, except as required by

paragraph (e) of this AD.

Note 2: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

(b) For Model BAe.125 series 800A (C–

29A) airplanes: Within 6 months after the

effective date of this AD, replace the

cadmium plated cone caps in the oxygen

system plumbing with improved cone caps,

and perform a detailed visual inspection of

the removed cone caps, tee-piece and sleeve

for evidence of flaking or corrosion; in

accordance with Raytheon Service Bulletin

SB 35–3171, dated September 1998. If any

flaking or corrosion is detected, prior to

further flight, clean the tee-piece and sleeve,

and perform an oxygen system flow check in

accordance with the service bulletin. If any

discrepancy is found during the flow check,

prior to further flight, repair the oxygen

system in accordance with the service

bulletin, except as required by paragraph (e)

of this AD.

(c) For Model BAe.125 series 800A and

800B airplanes and Model Hawker 800

airplanes: Within 6 months after the effective

date of this AD, replace the cadmium plated

cone caps in the oxygen system plumbing

with improved cone caps, and perform a

detailed visual inspection of the removed

cone caps, tee-piece and sleeve for evidence

of flaking or corrosion; in accordance with

Raytheon Service Bulletins SB 35–3034 or SB

35–3170, both dated September 1998, as

applicable. If any flaking or corrosion is

detected, prior to further flight, clean the teepiece and sleeve, and perform an oxygen

system flow check in accordance with the

service bulletin. If any discrepancy is found

during the flow check, prior to further flight,

repair the oxygen system in accordance with

the service bulletin, except as required by

paragraph (e) of this AD.

(d) For Model BAe.125 series 1000A and

1000B airplanes and Model Hawker 1000

series airplanes: Within 6 months after the

effective date of this AD, replace the

cadmium plated fittings in the oxygen system

plumbing with improved fittings, and

perform a detailed visual inspection of the

removed fittings and the pipe connections for

evidence of flaking or corrosion; in

accordance with Raytheon Service Bulletin

SB 35–3167 or SB 35–3168, both dated

September 1998, as applicable. If any flaking

or corrosion is detected, prior to further

flight, clean the pipe connections, and

perform an oxygen system flow check in

accordance with the service bulletin. If any

discrepancy is found during the flow check,

prior to further flight, repair the oxygen

system in accordance with the service

bulletin, except as required by paragraph (e)

of this AD.

(e) If any discrepancy is found during a

flow check required by paragraph (a), (b), (c),

or (d) of this AD and the applicable service

bulletin specifies to contact the manufacturer

for a repair disposition, prior to further flight,

repair the oxygen system in accordance with

a method approved by the Manager, Wichita

Aircraft Certification Office (ACO), FAA,

Small Airplane Directorate.

Alternative Methods of Compliance

(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, Wichita

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Wichita ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

Special Flight Permits

(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.

Incorporation by Reference

(h) Except as provided by paragraph (e) of

this AD, the actions shall be done in

accordance with Raytheon Service Bulletin

SB 35–3169, dated September 1998;

Raytheon Service Bulletin SB 35–3171, dated

September 1998; Raytheon Service Bulletin

SB 35–3034, dated September 1998;

Raytheon Service Bulletin SB 35–3170, dated

September 1998; Raytheon Service Bulletin

SB 35–3167, dated September 1998; or

Raytheon Service Bulletin SB 35–3168, dated

September 1998; 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

Raytheon Aircraft Company, Manager Service

Engineering, Hawker Customer Support

Department, P.O. Box 85, Wichita, Kansas

67201–0085. Copies may be inspected at the

FAA, Transport Airplane Directorate, 1601

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

the Small Airplane Directorate, Wichita

Aircraft Certification Office, 1801 Airport

Road, Room 100, Mid-Continent Airport,

Wichita, Kansas; or at the Office of the

Federal Register, 800 North Capitol Street,

NW., suite 700, Washington, DC.

(i) This amendment becomes effective on

March 13, 2000.

Issued in Renton, Washington, on January

28, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–2410 Filed 2–4–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–23–AD; Amendment

39–11556; AD 2000–02–38]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, A300–600, and A310 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Airbus Model

A300, A300–600, and A310 series

airplanes, equipped with a welded

auxiliary power unit (APU) fuel feedline

adapter. That AD currently requires

repetitive dye penetrant inspections to

detect cracks, rupture, or fuel leaks of

the fuel feedline adapter; and

replacement of the adapter, if necessary.

That AD also provides for optional

terminating action for the repetitive

inspections. This amendment requires

accomplishment of the previously

optional terminating action. 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 fuel leakage in the APU

compartment, which could result in a

fire in the APU compartment.

DATES: Effective March 13, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 13,

2000.

The incorporation by reference of

certain other publications, as listed in

the regulations, was approved

previously by the Director of the Federal

Register as of October 7, 1991 (56 FR

47672, September 20, 1991).

ADDRESSES: 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 Federal Aviation

5752 Federal Register / Vol. 65, No. 25 / Monday, February 7, 2000 / Rules and Regulations

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:

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.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 91–20–07,

amendment 39–8041 (56 FR 47672,

September 20, 1991), which is

applicable to certain Airbus Model

A300, A300–600, and A310 series

airplanes, was published in the Federal

Register on October 6, 1999 (64 FR

54249). The action proposed to continue

to require repetitive dye penetrant

inspections to detect cracks, rupture, or

fuel leaks of the fuel feedline adapter,

and replacement of the adapter, if

necessary. The action also proposed to

continue to require verification of the

correct torque values of the starter motor

cable terminals and the generator cable

terminals. The action also proposed to

require accomplishment of the

previously optional terminating action.

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.

One commenter requests clarification

concerning the relationship between the

adapter part number identified in the

referenced French airworthiness

directive and Airbus service bulletin

and the adapter part number referred to

in the Airbus Illustrated Parts Catalog

(IPC). The commenter has already

modified its auxiliary power units

(APU) to incorporate the adapter [part

number (P/N) A4937021700200]

specified in the service bulletin. The

Airbus IPC suggests an alternative P/N

for the adapter, i.e., P/N

A4937021700400; yet the IPC makes no

reference to any supersedure, nor does

it refer to a service bulletin authorizing

that P/N. The commenter asks whether

the installation of an adapter having

either P/N is acceptable for compliance

with the French airworthiness directive

and this proposed AD.

The FAA concurs that clarification is

necessary. Airbus has advised the FAA

that the only difference between the two

referenced P/N’s is that the tolerance for

the B-nut thread of the adapter having

P/N A4937021700400 has been

modified following service experience.

P/N A4937021700400 is installed on

airplanes by Airbus Modification 10323

and is two-way interchangeable with P/

N A4937021700200. Airbus advises that

an adapter having either P/N will fully

comply with the intent of the French

airworthiness directive. The FAA has

determined that installation of an

adapter having either P/N will

adequately address the unsafe condition

identified in this AD. A NOTE has been

added to the final rule to state that

installation of an adapter having P/N

A4937021700400 is also acceptable for

compliance with the requirements of

paragraph (b) of the AD.

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 change

previously described. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

Cost Impact

There are approximately 165

airplanes of U.S. registry that will be

affected by this AD.

The actions that are currently

required by AD 91–20–07 take

approximately 2 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

currently required actions on U.S.

operators is estimated to be $120 per

airplane.

The new actions that are required by

this new AD will take approximately 2

work hours per airplane to accomplish,

at an average labor rate of $60 per work

hour. Required parts will cost

approximately $274 per airplane. Based

on these figures, the cost impact of the

new requirements of this AD on U.S.

operators is estimated to be $394 per

airplane.

The cost impact figures discussed

above are 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

removing amendment 39–8041 (56 FR

47672, September 20, 1991), and by

adding a new airworthiness directive

(AD), amendment 39–11556, to read as

follows:

2000–02–38 Airbus Industrie: Amendment

39–11556. Docket 99–NM–23–AD.

Supersedes AD 91–20–07, Amendment

39–8041.

Applicability: Model A300, A300–600, and

A310 series airplanes; certificated in any

category; equipped with an auxiliary power

unit (APU) fuel feedline adapter, P/N

A4937021700000 (welded configuration).

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 (e) of this AD.

Federal Register / Vol. 65, No. 25 / Monday, February 7, 2000 / Rules and Regulations 5753

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 an APU compartment fire,

accomplish the following:

Restatement of Requirements of AD 91–20–

07, Amendment 39–8041

Repetitive Inspections

(a) Within 100 hours time-in-service after

October 7, 1991 (the effective date of AD 91–

20–07, amendment 39–8041), and thereafter

at intervals not to exceed 400 hours time-inservice: Perform a dye penetrant inspection

to detect cracks, rupture or fuel leaks at the

weld of the fuel feedline adapter, in

accordance with Airbus Industrie All

Operators Telex (AOT) 49–01, Issue 3, dated

April 25, 1991. If cracks, rupture, or fuel

leaks are found, replace the adapter with an

improved, non-welded one-piece-body

adapter prior to the next APU operation, or

placard the APU inoperative until the

adapter is replaced with the improved

adapter, in accordance with Airbus Industrie

Service Bulletin A300–49–0049, A300–49–

6009, or A310–49–2012; all dated July 12,

1991; as applicable.

(b) Within 100 hours time-in-service after

October 7, 1991, verify the correct torque

values of the starter motor cable terminals

and the generator cable terminals in

accordance with Airbus Industrie All

Operators Telex (AOT) 49–01, Issue 3, dated

April 25, 1991. Correct any torque value

discrepancies prior to further flight, in

accordance with the AOT.

New Requirements of This AD

Installation

(c) Within 15 months after the effective

date of this AD, install an improved APU fuel

feedline adapter in accordance with the

Accomplishment Instructions of Airbus

Service Bulletin A300–49–0049, Revision 1

(for Model A300 series airplanes); A300–49–

6009, Revision 1 (for Model A300–600 series

airplanes); or A310–49–2012, Revision 1 (for

Model A310 series airplanes); all dated

November 28, 1991; as applicable. Such

installation constitutes terminating action for

the requirements of this AD.

Note 2: Although the service bulletins

referenced in paragraph (b) of this AD specify

installation of an APU fuel feedline adapter

having part number P/N A4937021700200,

installation of an adapter having P/N

A4937021700400 is also acceptable for

compliance with the requirements of that

paragraph.

Spares

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

person shall install an APU fuel feedline

adapter, P/N A4937021700000 (welded

configuration), on any airplane.

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,

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

(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 actions shall be done in accordance

with the following Airbus All Operators

Telex (AOT) and Airbus service bulletins:

Service information referenced and date Page No. Revision level shown on

page Date shown on page

AOT 49–01, Issue 3, April 25, 1991 ................................... 1–3 ..................................... 3 ......................................... April 25, 1991.

A300–49–0049, July 12, 1991 ............................................ 1–11 ................................... Original ............................... July 12, 1991.

A300–49–0049, Revision 1, November 28, 1991 ............... 1–4, 7, 8, 11 ....................... 1 ......................................... November 28, 1991.

5, 6, 9, 10 ........................... Original ............................... July 12, 1991.

A300–49–6009, July 12, 1991 ............................................ 1–9 ..................................... Original ............................... July 12, 1991.

A300–49–6009, Revision 1, November 28, 1991 ............... 1–6, 9 ................................. 1 ......................................... November 28, 1991.

7, 8 ..................................... Original ............................... July 12, 1991.

A310–49–2012, July 12, 1991 ............................................ 1–11 ................................... Original ............................... July 12, 1991.

A310–49–2012, Revision 1, November 28, 1991 ............... 1–4, 7, 8, 11 ....................... 1 ......................................... November 28, 1991.

5, 6, 9, 10 ........................... Original ............................... July 12, 1991.

(1) The incorporation by reference of

Airbus Service Bulletin A300–49–0049,

Revision 1, dated November 28, 1991; Airbus

Service Bulletin A300–49–6009, Revision 1,

dated November 28, 1991; and Airbus

Service Bulletin A310–49–2012, Revision 1,

dated November 28, 1991; is approved by the

Director of the Federal Register in accordance

with 5 U.S.C. 552(a) and 1 CFR part 51.

(2) The incorporation by reference of

Airbus All Operators Telex (AOT) 49–01,

Issue 3, dated April 25, 1991; Airbus Service

Bulletin A300–49–0049, dated July 12, 1991;

Airbus Service Bulletin A300–49–6009,

dated July 12, 1991; and Airbus Service

Bulletin A310–49–2012; dated July 12, 1991;

was approved previously by the Director of

the Federal Register as of October 7, 1991 (56

FR 47672, September 20, 1991).

(3) 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 98–480–

269(B), dated December 2, 1998.

(h) This amendment becomes effective on

March 13, 2000.

Issued in Renton, Washington, on January

31, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–2469 Filed 2–4–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–88–AD; Amendment

39–11558; AD 2000–03–01]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–100 and Ø200 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 747–

100 and ¥200 series airplanes, that

requires repetitive inspections of the