Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations 34569

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:

98–13–20 Rolls-Royce Limited, Aero

Division-Bristol, N.E.C.M.A.:

Amendment 39–10609. Docket 98–ANE–

12–AD.

Applicability: Rolls-Royce Limited (R–R),

Aero Division-Bristol, S.N.E.C.M.A.,

Olympus 593 Mk. 610–14–28 turbojet

engines, installed on but not limited to

British Aerospace/Aerospatiale Concorde

series aircraft.

Note 1: This airworthiness directive (AD)

applies to each engine 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 engines 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 combustion chamber

detachment, which could result in an inflight

engine shutdown or an engine fire,

accomplish the following:

(a) At the next combustor exposure after

the effective date of this AD, accomplish the

following in accordance with the

Accomplishment Instructions of R–R Service

Bulletin (SB) No. OL.593–72–9038–417,

dated June 26, 1996:

(1) Perform a radiological inspection of the

combustion chamber No. 2 outer cooling ring

scoop circumferential and axial weld for

weld quality.

(2) If the weld quality does not meet the

standards described in the SB, reweld and

then perform an additional radiological

inspection for weld quality prior to return to

service.

(b) At the next combustor exposure after

the effective date of this AD, accomplish the

following in accordance with the

Accomplishment Instructions of R–R SB No.

OL.593–72–9048–424, dated April 25, 1997:

(1) Perform an inspection of the

combustion chamber No. 2 inner and outer

cooling ring for web length.

(2) If the web length is acceptable within

the limits described in the SB, mark the letter

‘‘T’’ adjacent to the part number.

(3) If the web length is not acceptable

within the limits described in the SB, remove

the combustion chamber from service and

replace affected components with serviceable

parts prior to return to service.

(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, Engine

Certification Office. Operators shall submit

their requests through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(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 aircraft to

a location where the inspection requirements

of this AD can be accomplished.

(e) The actions required by this AD shall

be performed in accordance with the

following R–R SBs:

Document No. Pages Date

OL.593–72–

9038–417.

1–3 June 26, 1996.

Total pages: 3.

OL.593–72–

9048–424.

1–4 April 25, 1997.

Total pages: 4.

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 Rolls-Royce, PO Box 3, Filton, Bristol

BS12 7QE, England; telephone 01–17–979–

1234, fax 01–17–979–7575. Copies may be

inspected at the FAA, New England Region,

Office of the Regional Counsel, 12 New

England Executive Park, Burlington, MA; or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(f) This amendment becomes effective on

July 10, 1998.

Issued in Burlington, Massachusetts, on

June 11, 1998.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 98–16270 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–16–AD; Amendment

39–10616; AD 98–13–25]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F.28 Mark 1000, 2000, 3000, and

4000 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Fokker Model F.28

Mark 1000, 2000, 3000, and 4000 series

airplanes, that currently requires an

inspection to detect free movement of

the actuator servo-valve sub-assembly of

the horizontal stabilizer actuator, and

replacement, if necessary. This

amendment adds a one-time inspection

to determine the residual strength of the

servo-valve sub-assembly of the

horizontal stabilizer actuator, and

replacement of the actuator with a new

or serviceable actuator, if necessary; and

eventual replacement of the horizontal

stabilizer actuator with an improved

actuator. 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 uncommanded

trimming or failure of the trim system of

the horizontal stabilizer, and

consequent reduced controllability of

the airplane.

DATES: Effective July 30, 1998.

The incorporation by reference of

Fokker Service Bulletin F28/27–183,

dated November 21, 1994, as listed in

the regulations, is approved by the

Director of the Federal Register as of

July 30, 1998.

The incorporation by reference of

Fokker Service Bulletin F28/27–180,

dated July 3, 1992, as listed in the

regulations, was approved by the

Director of the Federal Register as of

September 9, 1992 (57 FR 38432, August

25,1992).

ADDRESSES: The service information

referenced in this AD may be obtained

from Fokker Services B.V., Technical

Support Department, P.O. Box 75047,

1117 ZN Schiphol Airport, The

Netherlands. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,
34570 Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations

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 92–18–04,

amendment 39–8348 (57 FR 38432,

August 25, 1992), which is applicable to

certain Fokker Model F.28 Mark 1000,

2000, 3000, and 4000 series airplanes,

was published in the Federal Register

on April 27, 1998 (63 FR 20554). The

action proposed to continue to require

an inspection to detect free movement

of the actuator servo-valve sub-assembly

of the horizontal stabilizer actuator, and

replacement, if necessary. The action

proposed to add a one-time inspection

to determine the residual strength of the

servo-valve sub-assembly of the

horizontal stabilizer actuator, and

replacement of the actuator with a new

or serviceable actuator, if necessary; and

eventual replacement of the horizontal

stabilizer actuator with an improved

actuator.

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

There are approximately 27 airplanes

of U.S. registry that will be affected by

this AD.

The inspection that is currently

required by AD 92–18–04 takes

approximately 1 work hour per airplane

to accomplish, at an average labor rate

of $60 per work hour. Based on these

figures, the cost impact of the

previously required inspection on U.S.

operators is estimated to be $1,620, or

$60 per airplane.

The inspection that is required in this

new AD action will 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 new

inspection requirements of this AD on

U.S. operators is estimated to be $3,240,

or $120 per airplane.

The replacement required in this new

AD action will take approximately 8

work hours per airplane to accomplish,

at an average labor rate of $60 per work

hour. Required parts will be provided

by the manufacturer at no cost to the

operator. Based on these figures, the

cost impact of the replacement required

by this AD on U.S. operators is

estimated to be $12,960, or $480 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 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

removing amendment 39–8348 (57 FR

38432, August 25, 1992), and by adding

a new airworthiness directive (AD),

amendment 39–10616 to read as

follows:

98–13–25 Fokker: Amendment 39–10616.

Docket 98-NM–16-AD. Supersedes AD

92–18–04, Amendment 39–8348.

Applicability: Model F.28 Mark 1000,

2000, 3000, and 4000 series airplanes;

equipped with Menasco horizontal stabilizer

actuators having part number (P/N) 11100-

( ); 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 (e) 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 uncommanded trimming or

failure of the trim system of the horizontal

stabilizer, and consequent reduced

controllability of the airplane, accomplish

the following:

(a) Within 20 days after September 9, 1992

(the effective date of AD 92–18–04,

amendment 39–8348), perform an inspection

of the servo-valve sub-assembly rod-end

bearing and servo-valve sub-assembly for

movement, in accordance with Fokker

Service Bulletin F28/27–180, dated July 3,

1992.

(1) If the servo-valve sub-assembly rod-end

bearing and servo-valve sub-assembly move

freely within the load limits specified in the

service bulletin, reassemble and conduct a

functional test, in accordance with the

service bulletin.

(2) If the servo-valve sub-assembly rod-end

bearing or servo-valve sub-assembly require

higher loads for movement than specified in

the service bulletin, prior to further flight,

remove and replace the horizontal stabilizer

control unit with a serviceable control unit

that has been inspected and found to be

within the load limits of the service bulletin,

or that has been inspected and repaired in

accordance with Chapter 27–42–4 of the

Menasco Overhaul Manual (OHM), as revised

by Temporary Revision Number 3, dated July

10, 1992.

(b) Within 6 months after the effective date

of this AD, perform a one-time inspection to

determine the residual strength of the servovalve sub-assembly of the horizontal

stabilizer actuator, in accordance with Part 1

of the Accomplishment Instructions of
Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations 34571

Fokker Service Bulletin F28/27–183, dated

November 21, 1994. If any discrepancy is

found, prior to further flight, replace the

actuator with a new or serviceable actuator

in accordance with the service bulletin.

(c) Within 3 years after the effective date

of this AD, replace the horizontal stabilizer

actuator with an actuator that has been

modified and re-marked in accordance with

Part 2 of the Accomplishment Instructions of

Fokker Service Bulletin F28/27–183, dated

November 21, 1994.

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

person shall install a horizontal stabilizer

control unit on any airplane, unless the

horizontal stabilizer actuator has been

modified and re-marked in accordance with

Part 2 of the Accomplishment Instructions of

Fokker Service Bulletin F28/27–183, dated

November 21, 1994.

(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 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.

(f) 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.

(g) The actions shall be done in accordance

with Fokker Service Bulletin F28/27–180,

dated July 3, 1992, and Fokker Service

Bulletin F28/27–183, dated November 21,

1994.

(1) The incorporation by reference of

Fokker Service Bulletin F28/27–183, dated

November 21, 1994, 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

Fokker Service Bulletin F28/27–180, dated

July 3, 1992, was approved previously by the

Director of the Federal Register as of

September 9, 1992 (57 FR 38432, August 25,

1992).

(3) Copies may be obtained from Fokker

Services B.V., Technical Support

Department, P.O. Box 75047, 1117 ZN

Schiphol Airport, The Netherlands. 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 Dutch airworthiness directive 1992–007/

2(A), dated January 31, 1995.

(h) This amendment becomes effective on

July 30, 1998.

Issued in Renton, Washington, on June 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–16451 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–51–AD; Amendment

39–10617; AD 98–13–26]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace Model BAC 1–11 200 and

400 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all British Aerospace

Model BAC 1–11 200 and 400 series

airplanes, that requires repetitive

detailed visual inspections to detect

cracking in the trunnion fittings located

in the nose landing gear (NLG) bay of

the forward fuselage; and repair, 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 cracking

in the trunnion fittings of the NLG,

which could lead to collapse of the NLG

during takeoff and landing, and possible

injury to the flight crew and passengers.

DATES: Effective July 30, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 30,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from British Aerospace, Service

Support, Airbus Limited, P.O. Box 77,

Bristol BS99 7AR, England. 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 all British

Aerospace Model BAC 1–11 200 and

400 series airplanes was published in

the Federal Register on April 21, 1998

(63 FR 19682). That action proposed to

require repetitive detailed visual

inspections to detect cracking in the

trunnion fittings located in the nose

landing gear (NLG) bay of the forward

fuselage; and repair, 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

The FAA estimates that 42 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 1

work hour per airplane to accomplish

the required inspection, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the inspection required by this AD on

U.S. operators is estimated to be $2,520,

or $60 per airplane, per inspection

cycle.

The cost impact figure discussed

above is 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 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