37476 Federal Register / Vol. 65, No. 116 / Thursday, June 15, 2000 / Rules and Regulations

Nomenclature Part Number CIR Manual

Section CIR Manual Inspection CIR Manual

Hub, Turbine Intermediate Rear (Stage 2) ..................... ALL ..................................... 72–52–06 Insp/Check–02 ................... 51A357

For Engine Manual 51A342 only, insert the following table:

Nomenclature Part Number CIR Manual

Section CIR Manual Inspection CIR Manual

Hub, LPC Assembly ....................................................... ALL ..................................... 72–31–07 Insp/Check–02 ................... 51A357

Hub, Turbine Front Assembly (1st Stage) ...................... ALL ..................................... 72–52–05 Insp/Check–02 ................... 51A357

Hub, Turbine Rear (Stage 2) .......................................... ALL ..................................... 72–52–06 Insp/Check–02 ................... 51A357

For Engine Manual 51A345 only, insert the following table:

Nomenclature Part Number CIR Manual

Section CIR Manual Inspection CIR Manual

Hub, LPC Assembly ....................................................... ALL ..................................... 72–31–07 Insp/Check–02 ................... 51A370

Seal—Air, HPT, 1st Stage .............................................. ALL ..................................... 72–52–19 Insp/Check–02 ................... 51A750

Hub, Turbine Front Assembly (1st Stage) ...................... ALL ..................................... 72–52–05 Insp/Check–02 ................... 51A750

Seal—Air, HPT, 2nd Stage Assembly ............................ ALL ..................................... 72–52–22 Insp/Check–02 ................... 51A750

Hub, Turbine Rear Assembly (2nd Stage) ..................... ALL ..................................... 72–52–06 Insp/Check–02 ................... 51A750

For Engine Manual 51A751 only, insert the following table:

Nomenclature Part Number CIR Manual

Section CIR Manual Inspection CIR Manual

Hub, LPC Assembly ....................................................... ALL ..................................... 72–31–07 Insp/Check–02 ................... 51A750

Seal—Air, HPT, 1st Stage .............................................. ALL ..................................... 72–52–19 Insp/Check–02 ................... 51A750

Hub, Turbine Front Assembly (1st Stage) ...................... ALL ..................................... 72–52–05 Insp/Check–02 ................... 51A750

Seal—Air, HPT, 2nd Stage Assembly ............................ ALL ..................................... 72–52–22 Insp/Check–02 ................... 51A750

Hub, Turbine Rear Assembly (2nd Stage) ..................... ALL ..................................... 72–52–06 Insp/Check–02 ................... 51A750

(2) For the purpose of these mandatory

inspections, piece-part opportunity means:

(i) The part is considered completely

disassembled when accomplished in

accordance with the disassembly instructions

in the manufacturer’s engine manuals to

either the part detail or part assembly level

part numbers for the parts listed in the Tables

above; and

(ii) The part has accumulated more than

100 cycles in service since the last piece-part

opportunity inspection, provided that the

part was not damaged or related to the cause

for its removal from the engine.’’

(b) Except as provided in paragraph (c) of

this AD, and notwithstanding contrary

provisions in section 43.16 of the Federal

Aviation Regulations (14 CFR 43.16), these

mandatory inspections shall be performed

only in accordance with the Time Limits

Section of the manufacturer’s EM’s.

Alternative Method 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 Engine Certification

Office (ECO). Operators shall submit their

requests through an appropriate FAA

Principal Maintenance Inspector (PMI), who

may add comments and then send it to the

ECO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the ECO.

Ferry Flights

(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.

Continuous Airworthiness Maintenance

Program

(e) FAA-certificated air carriers that have

an approved continuous airworthiness

maintenance program in accordance with the

record keeping requirement of § 121.369(c) of

the Federal Aviation Regulations [14 CFR

121.369(c)] must maintain records of the

mandatory inspections that result from

revising the Time Limits Section of the EM’s

and the air carrier’s continuous airworthiness

program. Alternately, certificated air carriers

may establish an approved system of record

retention that provides a method for

preservation and retrieval of the maintenance

records that include the inspections resulting

from this AD, and include the policy and

procedures for implementing this alternate

method in the air carrier’s maintenance

manual required by § 121.369(c) of the

Federal Aviation Regulations [14 CFR

121.369(c)]; however, the alternate system

must be accepted by the appropriate PMI and

require the maintenance records be

maintained either indefinitely or until the

work is repeated. Records of the piece-part

inspections are not required under

§ 121.380(a)(2)(vi) of the Federal Aviation

Regulations [14 CFR 121.380(a)(2)(vi)]. All

other operators must maintain the records of

mandatory inspections required by the

applicable regulations governing their

operations.

Note 3: The requirements of this AD have

been met when the engine manual changes

are made and air carriers have modified their

continuous airworthiness maintenance plans

to reflect the requirements in the EM’s.

(f) This amendment becomes effective on

September 13, 2000.

Issued in Burlington, Massachusetts, on

June 5, 2000.

Diane S. Romanosky,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–14789 Filed 6–14–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–64–AD; Amendment

39–11784; AD 2000–12–06]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330 and A340 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

Federal Register / Vol. 65, No. 116 / Thursday, June 15, 2000 / Rules and Regulations 37477

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A330 and A340 series airplanes, that

requires repetitive inspections to check

the play of the eye-end of the piston rod

of the elevator servo-controls, 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 by this AD are

intended to detect and correct excessive

play of the eye-end of the piston rod of

the elevator servo-controls, which could

result in failure of the elevator servocontrol.

DATES: Effective July 20, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 20,

2000.

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

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) to

include an airworthiness directive (AD)

that is applicable to certain Airbus

Model A330 and A340 series airplanes

was published in the Federal Register

on April 11, 2000 (65 FR 19348). That

action proposed to require repetitive

inspections to check the play of the eyeend of the piston rod of the elevator

servo-controls, and follow-on corrective

actions, if necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

None of the 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. 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 2 work hours to

accomplish the required actions, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of this AD would be $120 per airplane,

per inspection cycle.

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

adding the following new airworthiness

directive:

2000–12–06 Airbus Industrie: Amendment

39–11784. Docket 2000–NM–64–AD.

Applicability: A330 and A340 series

airplanes, certificated in any category,

equipped with any ‘‘SAMM’’ elevator servocontrol having any part number SC4800–2

through SC4800–8 inclusive airplanes.

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 (b) 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 detect and correct excessive play of the

eye-end of the piston rod of the elevator

servo-controls, which could result in failure

of the elevator servo-control, accomplish the

following:

(a) Within 30 months since date of

manufacture of the airplane, or within 500

flight hours after the effective date of this AD,

whichever occurs later, perform an

inspection to check the play of the piston rod

eye-ends of the elevator servo-controls, in

accordance with Airbus Service Bulletin

A330–27–3062 (for Model A330 series

airplanes) or A340–27–4072 (for Model A340

series airplanes), both Revision 01, both

dated July 21, 1999. Thereafter, repeat the

inspection at intervals not to exceed 15

months.

(1) If any play that is 0.0059 inch (0.15

mm) or greater and less than 0.0118 inch

(0.30 mm) is detected: Prior to further flight,

replace the rod eye-end with a new

SARMA or NMB rod eye-end, in

accordance with the applicable service

bulletin.

(2) If any play that is 0.0118 inch (0.30

mm) or greater is detected: Prior to further

flight, perform a dye penetrant inspection to

detect cracking of the servo-control, in

accordance with the applicable service

bulletin.

(i) If no crack is detected: Prior to further

flight, replace the rod eye-end with a new

SARMA or NMB rod eye-end, in accordance

with the applicable service bulletin.

(ii) If any crack is detected: Prior to further

flight, replace the servo-control with a new

37478 Federal Register / Vol. 65, No. 116 / Thursday, June 15, 2000 / Rules and Regulations

servo-control, in accordance with the

applicable service bulletin.

Note 2: Accomplishment of an inspection

in accordance with Airbus Service Bulletin

A330–27–3062 (for Model A330 series

airplanes) or A340–27–4072 (for Model A340

series airplanes), both dated February 5,

1999; is considered acceptable for

compliance with the initial inspection

requirements of paragraph (a) of this AD.

Note 3: The Airbus service bulletins

reference SAMM Service Bulletin SC4800–

27–34–06, dated January 2, 1999, as an

additional source of service information for

accomplishment of the dye penetrant

inspection specified by paragraph (a)(2) of

this AD.

Alternative Methods of Compliance

(b) 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 4: 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

(c) 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

(d) The actions shall be done in accordance

with Airbus Service Bulletin A330–27–3062,

Revision 01, dated July 21, 1999; or Airbus

Service Bulletin A340–27–4072, Revision 01,

dated July 21, 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 5: The subject of this AD is addressed

in French airworthiness directives 2000–

025–109(B) R1 and 2000–024–135(B) R1,

both dated March 8, 2000.

(e) This amendment becomes effective on

July 20, 2000.

Issued in Renton, Washington, on June 7,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14882 Filed 6–14–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–51–AD; Amendment

39–11785; AD 2000–12–07]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB SF340A and SAAB 340B Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Saab Model SAAB

SF340A and SAAB 340B series

airplanes, that requires a one-time

inspection to detect corrosion and

scratches on the bearing housing

surfaces of the support assembly on the

main landing gear (MLG), and corrective

actions, 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 corrosion in the

inboard and outboard bearing housings

of the MLG support assembly, which

could result in fatigue cracks in the

support assembly and lead to failure of

the MLG.

DATES: Effective July 20, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 20,

2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Saab Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

Sweden. 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:

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) to

include an airworthiness directive (AD)

that is applicable to certain Saab Model

SAAB SF340A and SAAB 340B series

airplanes was published in the Federal

Register on January 5, 2000 (65 FR 395).

That action proposed to require a onetime inspection to detect corrosion and

scratches on the bearing housing

surfaces of the support assembly on the

main landing gear, and corrective

actions, if necessary.

Consideration of Comments Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the two

comments received.

Request To Include Optional Repair

Procedure to This AD

One commenter, an operator, requests

that the optional repair procedure,

included in a note in step 2.C.(1)(b)10

of the Accomplishment Instructions of

Saab Service Bulletin 340–57–036,

dated October 20, 1999, be added to the

proposed AD. That procedure specifies

certain options for follow-on repair

based on the depth and extent of

damage after rework. One option would

require repair of the main landing gear

(MLG) support assembly within 4,000

flight cycles after the inspection.

Another option would require

reinstalling the bearings for the MLG

assembly and continuing to operate the

airplane an additional 4,000 flight

cycles before the final repair is

accomplished. The commenter adds that

[without having these options] ‘‘we

foresee a serious maintenancescheduling issue’’ due to the large

number of Saab Model SAAB 340 series

airplanes in its fleet (presently 115).

The FAA concurs with the

commenter’s request to include in this

AD the two options specified in the

service bulletin. Although those options

were inadvertently omitted in the

proposed AD, both options are included

in this AD. The FAA has determined

that, for damage within certain limits

after rework, deferral of the final repair

of the MLG support assembly for 4,000

flight cycles will adequately address the

identified unsafe condition and is

acceptable for the requirements of this

AD.

Request To Revise Cost Estimate

One commenter states that ‘‘unless

there is a policy to address inspections

only and not include preparation,

corrective action, and close up costs, the

costs are underestimated in the NPRM.’’

The service bulletin includes detailed

costs for the actions specified, which

include access, inspection, corrective

actions, close up, and test. The

commenter adds that, if operators