29096 Federal Register / Vol. 63, No. 102 /Thursday, May 28, 1998 /Rules and Regulations

flight, perform rework or install new

components, as applicable, in accordance

with the service bulletin.

(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 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.

(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.

(d) The actions shall be done in accordance

with Saab Service Bulletin 2000–35–001,

dated February 20, 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,

Linkping, 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.

Note 3: The subject of this AD is addressed

in Swedish airworthiness directive (SAD) 1–

091, dated February 20, 1996.

(e) This amendment becomes effective on

July 2, 1998.

Issued in Renton, Washington, on May 18,

1998.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–13822 Filed 5–27–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–172–AD; Amendment

39–10544; AD 98–11–19]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 and A300–600 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A310 and A300–600 series airplanes,

that requires a visual inspection to

detect cracks in the aft mount beam

assembly of the engine; and replacement

of any cracked beam with a new beam

or beam assembly. This amendment also

requires a fluorescent penetrant

inspection to detect cracks in the aft

mount beam assembly of the engine,

and various follow-on actions. This

amendment is prompted by reports

indicating that, apparently due to

manufacturing defects during the

forging process, cracking was found in

two engine aft mount beams. The

actions specified by this AD are

intended to detect and correct such

cracking, which could result in reduced

structural integrity of the aft mount

beam assembly of the engine.

DATES: Effective July 2, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 2, 1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Pratt & Whitney, 400 Main Street,

East Hartford, Connecticut 06108. 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 A310 and A300–600 series

airplanes was published in the Federal

Register on April 1, 1997 (62 FR 15439).

That action proposed to require a visual

inspection to detect cracks in the aft

mount beam assembly of the engine;

and replacement of any cracked beam

with a new beam or beam assembly.

That action also proposed to require a

fluorescent penetrant inspection to

detect cracks in the aft mount beam

assembly of the engine, and various

follow-on actions.

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 supports the

proposed rule.

One commenter requests that the

proposed AD be revised to cite

accomplishment of Pratt & Whitney

Service Bulletin PW4MD11 A71–102,

Revision 3, dated August 30, 1995, as an

equivalent alternative to

accomplishment of Pratt & Whitney

Alert Service Bulletins PW4NAC A71–

149, Revision 1, dated August 30, 1995,

and PW7R4 A71–129, Revision 1, dated

August 30, 1995, as referenced in the

proposed AD.

The FAA concurs with the

commenter’s request to cite

accomplishment of Pratt & Whitney

Service Bulletin PW4MD11 A71–102,

Revision 3, dated August 30, 1995, as an

equivalent alternative to

accomplishment of Pratt & Whitney

Alert Service Bulletins PW4NAC A71–

149, Revision 1, dated August 30, 1995

or PW7R4 A71–129, Revision 1, dated

August 30, 1995. Pratt & Whitney Alert

Service Bulletins PW4NAC A71–149,

Revision 1, dated August 30, 1995, and

PW7R4 A71–129, Revision 1, dated

August 30, 1995, contain a Note that

states: ‘‘Service Bulletins PW4NAC

A71–149 (PW4000/AI), PW7R4 A71–

129 (JT9D–7R4/AI), and PW4MD11

A71–102 (PW4000/DAC) have been

issued to cover all aircraft.

Accomplishment of any one of these

Service Bulletins satisfies the same

intent of the other two.’’ The FAA has

revised this final rule to reflect this

change by adding a new Note to 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

The FAA estimates that 8 Airbus

Model A310 and A300–600 series

airplanes of U.S. registry will be affected

by this AD.

It will take approximately 2 work

hours per airplane to accomplish the

required visual inspection, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

visual inspection required by this AD on

U.S. operators is estimated to be $960,

or $120 per airplane.

It will take approximately 34 work

hours per airplane to accomplish the

required fluorescent penetrant

inspection, at an average labor rate of
Federal Register / Vol. 63, No. 102 /Thursday, May 28, 1998 /Rules and Regulations 29097

$60 per work hour. Based on these

figures, the cost impact of the

fluorescent penetrant inspection

required by this AD on U.S. operators is

estimated to be $16,320, or $2,040 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

adding the following new airworthiness

directive:

98–11–19 Airbus Industrie: Amendment

39–10544. Docket 96–NM–172–AD.

Applicability: Model A310 and A300–600

series airplanes, equipped with Pratt &

Whitney Model JT9D–7R4D1, JT9D–7R4E1,

JT9D–7R4H1, PW4151, PW4156A, or

PW4158 engines; 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 (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 detect and correct cracking in the aft

mount beam assembly of the engine, which

could result in reduced structural integrity of

the aft mount beam assembly, accomplish the

following:

(a) Within 500 flight hours after the

effective date of this AD, perform a visual

inspection to detect cracks in the aft mount

beam assembly of the engine, in accordance

with Part 1 of the Accomplishment

Instructions of Pratt & Whitney Alert Service

Bulletin PW7R4 A71–129, Revision 1, dated

August 30, 1995, or Pratt & Whitney Alert

Service Bulletin PW4NAC A71–149, Revision

1, dated August 30, 1995; as applicable.

(1) If no crack is detected, no further action

is required by this paragraph.

(2) If any crack is detected, prior to further

flight, replace the cracked beam with a new

beam or beam assembly, in accordance with

the applicable service bulletin.

(b) Within 4,000 flight cycles after the

effective date of this AD, perform a

fluorescent penetrant inspection to detect

cracks in the aft mount beam assembly of the

engine, in accordance with Part 2 of the

Accomplishment Instructions of Pratt &

Whitney Alert Service Bulletin PW7R4 A71–

129, Revision 1, dated August 30, 1995, or

Pratt & Whitney Alert Service Bulletin

PW4NAC A71–149, Revision 1, dated August

30, 1995; as applicable.

(1) If no crack is detected, prior to further

flight, perform an eddy current inspection to

detect cracks in the aft mount beam assembly

of the engine, in accordance with the

applicable service bulletin.

(i) If no crack is detected, prior to further

flight, reidentify the beam in accordance with

the applicable service bulletin.

(ii) If any crack is detected, prior to further

flight, replace the cracked beam with a new

beam or beam assembly, in accordance with

the applicable service bulletin.

(2) If any crack is detected, prior to further

flight, replace the cracked beam with a new

beam or beam assembly, in accordance with

the applicable service bulletin.

Note 2: Accomplishment of the actions

required by paragraphs (a) and (b) of this AD

in accordance with Pratt & Whitney Service

Bulletin PW4MD11 A71–102, Revision 3,

dated August 30, 1995, is considered to be

acceptable for compliance with those

paragraphs.

(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,

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.

(d) 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.

(e) The actions shall be done in accordance

with the following Pratt & Whitney Alert

Service Bulletins, which contain the

following list of effective pages:

Service bulletin referenced and date Page number shown on page Revision level shown

on page Date shown on page

PW7R4 A71–129, Revision 1, August 30,

1995.

1, 4, 12, 17–21, 23, 25–32 ............................... 1 ................................ August 30, 1995.

2, 3, 5–11, 13–16, 22, 24 ................................. Original ...................... May 30, 1995.

PW4NAC A71–149, Revision 1, August 30,

1995.

1, 2, 4, 12, 17–21 25–32 .................................. 1 ................................ August 30, 1995.

3, 5–11, 13–16 22–24 ...................................... Original ...................... May 30, 1995.
29098 Federal Register / Vol. 63, No. 102 /Thursday, May 28, 1998 /Rules and Regulations

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 Pratt & Whitney, 400 Main Street, East

Hartford, Connecticut 06108. 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 96–020–

195(B), dated January 31, 1996.

(f) This amendment becomes effective on

July 2, 1998.

Issued in Renton, Washington, on May 18,

1998.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–13821 Filed 5–27–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–121–AD; Amendment

39–10541; AD 98–11–16]

RIN 2120–AA64

Airworthiness Directives; Dornier

Luftfahrt GmbH Models 228–100, 228–

101, 228–200, 228–201, 228–202, and

228–212 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Dornier Luftfahrt

GmbH (Dornier) Models 228–100, 228–

101, 228–200, 228–201, 228–202, and

228–212 airplanes. This AD requires

modifying the logic in the failure

detection circuits of the landing gear

uplock switches. This AD is the result

of mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for Germany.

The actions specified by this AD are

intended to prevent a false warning

indication of landing gear failure

because of the design of the landing gear

warning system, which could result in

incorrect actions from the pilot based on

the warning indications.

DATES: Effective July 11, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 11,

1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

Daimler-Benz Aerospace, Dornier,

Product Support, P.O. Box 1103, D–

82230 Wessling, Federal Republic of

Germany; telephone: (08153) 300;

facsimile: (08153) 302985. This

information may also be examined at

the Federal Aviation Administration

(FAA), Central Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 97–CE–121–AD, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106; or at the Office of the Federal

Register, 800 North Capitol Street, NW,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Karl Schletzbaum, Aerospace Engineer,

FAA, Small Airplane Directorate, 1201

Walnut, suite 900, Kansas City, Missouri

64106; telephone: (816) 426–6934;

facsimile: (816) 426–2169.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This

AD

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to include an AD that would

apply to certain Dornier Models 228–

100, 228–101, 228–200, 228–201, 228–

202, and 228–212 airplanes was

published in the Federal Register as a

notice of proposed rulemaking (NPRM)

on March 26, 1998 (63 FR 14658). The

NPRM proposed to require modifying

the logic in the failure detection circuits

of the landing gear uplock switches.

Accomplishment of the proposed action

as specified in the NPRM would be in

accordance with Dornier Service

Bulletin No. SB–228–215, Revision No.

1, dated January 31, 1995.

The NPRM was the result of

mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for Germany.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposed rule or the FAA’s

determination of the cost to the public.

The FAA’s Determination

After careful review of all available

information related to the subject

presented above, the FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial corrections. The FAA has

determined that these minor corrections

will not change the meaning of the AD

and will not add any additional burden

upon the public than was already

proposed.

Cost Impact

The FAA estimates that 26 airplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

32 workhours per airplane to

accomplish this action, and that the

average labor rate is approximately $60

an hour. Based on these figures, the total

cost impact of this AD on U.S. operators

is estimated to be $49,920, or $1,920 per

airplane.

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 copy of the final

evaluation prepared for this action is

contained in the Rules Docket. A copy

of it may be obtained by contacting 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 a new airworthiness directive

(AD) to read as follows:

98–11–16 Dornier Luftfahrt GMBH:

Amendment 39–10541; Docket No. 97–

CE–121–AD.

Applicability: Models 228–100, 228–101,

228–200, 228–201, 228–202, and 228–212