Federal Register / Vol. 62, No. 66 / Monday, April 7, 1997 / Rules and Regulations 16475

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 1 CASA

Model CN–235 series airplane of U.S.

registry will be affected by this AD, that

it will take approximately 12 work

hours per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour.

Required parts will cost approximately

$1,485 per airplane. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be $2,205

per airplane.

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

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:

97–07–13 Construcciones Aeronauticas,

S.A. (CASA): Amendment 39–9987.

Docket 96-NM–127-AD.

Applicability: Model CN–235 series

airplanes; as listed in CASA Service Bulletin

SB–235–53–21M, Revision 1, dated

November 21, 1994 (military airplanes), and

CASA Service Bulletin SB–235–53–21,

Revision 3, dated November 30, 1994 (nonmilitary airplanes); 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 (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 prevent fatigue from causing the center

wing attachment rods to fail, which

consequently could reduce the structural

integrity of the wing-to-fuselage attachment,

accomplish the following:

(a) Prior to the accumulation of 16,000 total

landings, replace center wing attachment

rods having CASA part number (P/N) 35–

22058–0003 or 35–22067–0001 with new

rods having CASA P/N 35–22067–0003, in

accordance with CASA Service Bulletin SB–

235–53–21M, Revision 1, dated November

21, 1994 (for military airplanes); or CASA

Service Bulletin SB–235–53–21, Revision 3,

dated November 30, 1994 (for non-military

airplanes); as applicable.

(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,

Standardization Branch, ANM–113, 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, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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 replacement shall be done in

accordance with CASA Service Bulletin SB–

235–53–21M, Revision 1, dated November

21, 1994; or CASA Service Bulletin SB–235–

53–21, Revision 3, dated November 30, 1994;

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 Construcciones Aeronauticas,

S.A., Getafe, Madrid, Spain. 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.

(e) This amendment becomes effective on

May 12, 1997.

Issued in Renton, Washington, on March

27, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–8423 Filed 4–4–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–ANE–56; Amendment 39–

9978; AD 97–07–04]

RIN 2120–AA64

Airworthiness Directives; Rolls-Royce

plc RB.211–524 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Rolls-Royce plc RB.211–

524 series turbofan engines, that

requires initial and repetitive borescope

inspections of the head section and

meterpanel assembly of the combustion

liner, and replacement, if necessary,

with serviceable parts. In addition, this

AD allows an optional installation of a

front combustion liner with a

strengthened head section as a

terminating action to the inspection
16476 Federal Register / Vol. 62, No. 66 / Monday, April 7, 1997 / Rules and Regulations

requirements. This amendment is

prompted by reports of engine fires due

to premature engine combustor distress.

The actions specified by this AD are

intended to prevent engine combustor

liner deterioration due to thermal

fatigue, which can result in combustor

liner and case burn-through and engine

fire.

DATES: Effective June 6, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 6,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Rolls-Royce North America, Inc.,

2001 South Tibbs Ave., Indianapolis, IN

46241; telephone (317) 230–3995, fax

(317) 230–4743. This information may

be examined at the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

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.

FOR FURTHER INFORMATION CONTACT:

Eugene Triozzi, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7148,

fax (617) 238–7199.

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 Rolls-Royce plc (R–

R) RB.211–524 series turbofan engines

was published in the Federal Register

on November 13, 1996 (61 FR 58147).

That action proposed to require initial

and repetitive borescope inspections of

the head section and meterpanel

assembly of the combustion liner, and

replacement, if necessary, with

serviceable parts. In addition, this AD

proposed an optional installation of a

front combustion liner with a

strengthened head section C263 material

as a terminating action to the inspection

requirements.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. Since publication

of the NPRM, R–R has issued Revision

3 to Service Bulletin No. RB.211–72–

B482, dated September 27, 1996, that

differs from Revision 2, referenced in

the NPRM, by editorial changes only.

This final rule references Revision 3 of

the SB. The FAA has determined that

air safety and the public interest require

the adoption of the rule with the change

described previously.

There are approximately 250 engines

of the affected design in the worldwide

fleet. There are currently no domestic

operators of Rolls-Royce plc RB.211–

524G or –524H series turbofan engines.

The FAA estimates that it will take

approximately 8 work hours per engine

to accomplish the required actions, and

that the average labor rate is $60 per

work hour. Based on these figures, the

cost impact per engine per inspection is

estimated to be $480.

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:

97–07–04 Rolls-Royce plc: Amendment 39–

9978. Docket 95–ANE–56.

Applicability: Rolls-Royce plc (R–R)

Models RB.211–524G and –524H turbofan

engines that have not been modified in

accordance with R–R Service Bulletin (SB)

No. RB.211–72–9764, Revision 2, dated

November 10, 1995, installed on but not

limited to Boeing 747–400 and 767–300

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 (d)

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 engine combustor liner

deterioration due to thermal fatigue, which

can result in combustor liner and case burnthrough and engine fire, accomplish the

following:

(a) Perform initial and repetitive borescope

inspections of the engine combustor liner

head section in accordance with the intervals

listed in Section 1.C. Compliance (1), and the

procedures described in Section 1.D. Action

(1) of R–R SB No. RB.211–72–B482, Revision

3, dated September 27, 1996. Prior to further

flight, remove combustors that do not meet

the return to service criteria specified in

Section 1.E. Acceptance Limits of the SB and

replace with serviceable parts.

(b) Perform initial and repetitive borescope

inspections of the meterpanel in accordance

with the intervals listed in Section 1.C.

Compliance (2), and the procedures

described in Section 1.D. Action (2) of R–R

SB No. RB.211–72–B482, Revision 3, dated

September 27, 1996. Prior to further flight,

remove combustors that do not meet the

return to service criteria specified in Section

1.E. Acceptance Limits of the SB and replace

with serviceable parts.

(c) Installation of a front combustion liner

with a strengthened head section in C263

material in accordance with R–R SB No.

RB.211–72–9764, Revision 2, dated

November 10, 1995, constitutes terminating

action to the inspection requirements of this

AD.

(d) 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. The request should be

forwarded through an appropriate FAA

Principal Maintenance Inspector, who may
Federal Register / Vol. 62, No. 66 / Monday, April 7, 1997 / Rules and Regulations 16477

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.

(e) 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 requirements of this AD

can be accomplished.

(f) The actions required by this AD shall be

done in accordance with the following R–R

SBs:

Document No. Pages Revision Date

RB.211–72–B482 ................................................................................................................ 1 3 ....................... September 27, 1996.

2 2 ....................... March 11, 1996.

3 3 ....................... September 27, 1996.

4 2 ....................... March 11, 1996.

5 3 ....................... September 27, 1996.

6 2 ....................... March 11, 1996.

7–8 3 ....................... September 27, 1996.

9 2 ....................... March 11, 1996.

Total Pages: 9.

RB.211–72–9764 ................................................................................................................. 1 2 ....................... November 10, 1995.

2 Original ............. August 20, 1993.

3 2 ....................... November 10, 1995.

4–6 1 ....................... August 25, 1995.

7–30 Original ............. August 20, 1993.

Supplement ......................................................................................................................... 1 Original ............. August 20, 1993.

Total Pages: 31.

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 North America, Inc., 2001

South Tibbs Ave., Indianapolis, IN 46241;

telephone (317) 230–3995, fax (317) 230–

4743. Copies may be inspected at the FAA,

New England Region, Office of the Assistant

Chief 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.

(g) This amendment becomes effective on

June 6, 1997.

Issued in Burlington, Massachusetts, on

March 26, 1997.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 97–8474 Filed 4–4–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–ANE–43; Amendment 39–

9977; AD 97–01–04]

RIN 2120–AA64

Airworthiness Directives; Textron

Lycoming and Superior Air Parts, Inc.

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule, request for

comments.

SUMMARY: This document publishes in

the Federal Register an amendment

adopting Airworthiness Directive (AD)

97–01–04 that was sent previously to all

known U.S. owners and operators of

certain Textron Lycoming TIO–540,

LTIO–540, and IO–540 series

reciprocating engines with certain

Superior Air Parts, Inc. Parts

Manufacture Approval (PMA)

replacement cylinder assemblies

installed by individual letters. This AD

requires removal from service of

affected cylinder assemblies for higher

time cylinder assemblies and

replacement with serviceable parts, and

initial and repetitive dye penetrant

inspections for mid-time cylinder

assemblies, or replacement with

serviceable parts. This amendment is

prompted by a report of an inflight

engine failure of a Textron Lycoming

TIO–540 reciprocating engine with

affected Superior Air Parts, Inc. PMA

cylinder assemblies installed. The

actions specified by this AD are

intended to prevent cylinder head

separation, inflight loss of power,

possible engine failure, and fire.

DATES: Effective April 22, 1997 to all

persons except those persons to whom

it was made immediately effective by

priority letter AD 97–01–04, issued on

December 27, 1996, which contained

the requirements of this amendment.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 22,

1997.

Comments for inclusion in the Rules

Docket must be received on or before

June 6, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

96–ANE–43, 12 New England Executive

Park, Burlington, MA 01803–5299.

The applicable service information

may be obtained from Superior Air

Parts, Inc., 14280 Gillis Road, Dallas, TX

75244–3792; telephone (800) 400–5949,

fax (972) 702–8723. This information

may be examined at the FAA, New

England Region, Office of the Assistant

Chief 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.

FOR FURTHER INFORMATION CONTACT: M.

Monica Merritt, Aerospace Engineer,

Special Certification Office, FAA,

Rotorcraft Directorate, 2601 Meacham

Blvd., Ft. Worth, TX 76137–4298;

telephone (817) 222–5196, fax (817)

222–5136.

SUPPLEMENTARY INFORMATION: On

December 27, 1996, the Federal

Aviation Administration (FAA) issued

priority letter airworthiness directive

(AD) 97–01–04, applicable to Textron

Lycoming Models TIO–540–A2C, –J2B,

–F2BD, –J2BD, –N2BD, –R2AD, –S1AD,

and LTIO–540–J2B, –F2BD, –J2BD,

N2BD, –R2AD, and IO–540–M1B5D

reciprocating engines, with Superior Air

Parts, Inc. Parts Manufacture Approval

(PMA) part number SL54000–A1, –A2,

–A2P, –A20P, and A21P series

replacement cylinder assemblies

installed, with serial numbers 001

through 650. That action was prompted

by a report from the Australian Civil

Aviation Authority (CAA) of a New

Piper Company Model PA31–350

aircraft, with a Textron Lycoming TIO–

540 engine installed, that suffered an

inflight engine failure. An examination