35814 Federal Register / Vol. 65, No. 109 / Tuesday, June 6, 2000 / Rules and Regulations

1. A minimum threat of 100 volts rms

per meter electric field strength from 10

KHz to 18 GHz.

a. The threat must be applied to the

system elements and their associated

wiring harnesses without the benefit of

airframe shielding.

b. Demonstration of this level of

protection is established through system

tests and analysis.

2. A threat external to the airframe for

both of the following field strengths for

the frequency ranges indicated. Both

peak and average field strength

components from the Table are to be

demonstrated.

Frequency

Field strength

(volts per meter)

Peak Average

10 kHz–100 kHz ............. 50 50

100 kHz–500 kHz ........... 50 50

500 kHz–2 MHz .............. 50 50

2 MHz–30 MHz ............... 100 100

30 MHz–70 MHz ............. 50 50

70 MHz–100 MHz ........... 50 50

100 MHz–200 MHz ......... 100 100

200 MHz–400 MHz ......... 100 100

400 MHz–700 MHz ......... 700 50

700 MHz–1 GHz ............. 700 100

1 GHz–2 GHz ................. 2000 200

2 GHz–4 GHz ................. 3000 200

4 GHz–6 GHz ................. 3000 200

6 GHz–8 GHz ................. 1000 200

8 GHz–12 GHz ............... 3000 300

12 GHz–18 GHz ............. 2000 200

18 GHz–40 GHz ............. 600 200

The field strengths are expressed in terms

of peak of the root-mean-square (rms) over

the complete modulation period.

The threat levels identified above are

the result of an FAA review of existing

studies on the subject of HIRF, in light

of the ongoing work of the

Electromagnetic Effects Harmonization

Working Group of the Aviation

Rulemaking Advisory Committee.

Discussion of Comments

Notice of proposed special conditions

No. 25–00–01–SC for the Raytheon

Aircraft Model 4000 airplanes was

published in the Federal Register on

March 14, 2000 (65 FR 13703). No

comments were received, and the

special conditions are adopted as

proposed.

Applicability

As discussed above, these special

conditions are applicable to the Model

4000 airplane. Should Raytheon Aircraft

Company apply at a later date for a

change to the type certificate to include

another model incorporating the same

novel or unusual design features, these

special conditions would apply to that

model as well under the provisions of

§ 21.101(a)(1).

Conclusion

This action affects only certain design

features on the Raytheon Aircraft

Company Model 4000 airplanes. It is not

a rule of general applicability and

affects only the applicant who applied

to the FAA for approval of these features

on the airplane.

List of Subjects in 14 CFR Part 25

Aircraft, Aviation safety, Reporting

and recordkeeping requirements.

The authority citation for these

special conditions is as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701,

44702, 44704.

The Special Conditions

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the following special

conditions are issued as part of the type

certification basis for Raytheon Aircraft

Company Model 4000 airplanes.

1. Protection from Unwanted Effects

of High-Intensity Radiated Fields

(HIRF). Each electrical and electronic

system that performs critical functions

must be designed and installed to

ensure that the operation and

operational capability of these systems

to perform critical functions are not

adversely affected when the airplane is

exposed to high intensity radiated

fields.

2. For the purpose of this special

condition, the following definition

applies:

Critical Functions. Functions whose

failure would contribute to or cause a

failure condition that would prevent the

continued safe flight and landing of the

airplane.

Issued in Renton, Washington, on May 22,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14156 Filed 6–5–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94–ANE–16–AD; Amendment

39–11758; AD 2000–11–10]

RIN 2120–AA64

Airworthiness Directives; Rolls-Royce

plc RB211 Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD)

applicable to certain Rolls-Royce plc (R–

R) RB211 series turbofan engines. That

AD currently requires the removal from

service of intermediate pressure (IP)

compressor stage 6–7 rotor shafts that

exceed reduced cyclic life limits. This

amendment requires further reduction

of cyclic life limits and introduction of

new reduced cyclic bands for rework.

This action is prompted by additional

stress analysis conducted following

failure of an IP compressor stage 6 disk.

The actions specified by this AD are

intended to prevent an uncontained

engine failure due to rupture of an IP

compressor stage 6–7 rotor shaft.

DATES: Effective August 7, 2000. The

incorporation by reference of certain

publications listed in the rule is

approved by the Director of the Federal

Register as of August 7, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Rolls-Royce plc, Technical

Publications Department, P.O. Box 31,

Derby, DE24 8BJ, UK, telephone 011–

44–1332–242424. This information may

be examined at the Federal Aviation

Administration (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.

FOR FURTHER INFORMATION CONTACT:

Jason Yang, Aerospace Engineer, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7747, fax

(781) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 94–18–03,

Amendment 39–9016 (59 FR 46536),

applicable to R–R RB211–22B and –524

series turbofan engines, was published

in the Federal Register on August 31,

1999 (64 FR 47447). That action

proposed to require the removal from

service of IP compressor stage 6–7 rotor

shafts that exceed reduced cyclic life

limits.

Conclusion

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. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed.

Federal Register / Vol. 65, No. 109 / Tuesday, June 6, 2000 / Rules and Regulations 35815

Economic Analysis

There are approximately 1,300

engines of the affected design in the

worldwide fleet. The manufacturer has

advised the FAA that there are 228

engines installed on aircraft of U.S.

registry that will be affected by this AD.

It will take approximately 24 work

hours or $1,440 per engine to

accomplish the proposed rework

actions, if rework of the rotor shafts is

selected. Otherwise, to maintain the

record of the cyclic life of IP compressor

stage 6–7 rotor shafts has minimum

economic impact on U.S operators.

Based on these figures, the total cost

impact of the AD on U.S. operators is

estimated to be less than $330,000.

Regulatory Impact

This final rule does not have

federalism implications, as defined in

Executive Order 13132, because it does

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. Accordingly, the

FAA has not consulted with state

authorities prior to publication of this

final rule.

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 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 39–9016 (59 FR

46536, September 9, 1994) and by

adding a new airworthiness directive to

read as follows:

2000–11–10 Rolls-Royce plc: Amendment

39–11758. Docket No. 94–ANE–16–AD.

Supersedes AD 94–18–03, Amendment

39–9016.

Applicability

Rolls-Royce plc (R–R) Model RB211–22B

and –524 series turbofan engines, not

incorporating new intermediate pressure (IP)

compressor stage 6–7 rotor shafts assemblies

with redesigned stage 6 disks in accordance

with R–R Service Bulletin (SB) No. RB.211–

72–9993, dated August 26, 1994. These

engines are installed on but not limited to

Boeing 747 series and 767 series, and

Lockheed L–1011 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 (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 previously

accomplished.

To prevent an uncontained engine failure

due to rupture of an IP compressor stage 6–

7 rotor shaft, accomplish the following:

Corrective Action

(a) For IP compressor stage 6–7 rotor shafts

that have not been reworked in accordance

with SB RB.211–72–9594, Revision 8, dated

January 14, 1999, Revision 7, dated

September 16, 1994, Revision 6, dated

August 12, 1994, or Revision 5, dated

February 12, 1993, remove the rotor shafts

prior to exceeding the life limits established

in Table 1 of this AD under sub-title ‘‘Pre

SB72–9594’’ and replace with serviceable

parts.

TABLE 1

Engine mark and mod

standard

Pre SB72–9594 Rework bands Post SB72–9594 Post SB72–9618

Life limits

through

12/31/00

Life limits

after

12/31/00

Life limits

after

12/31/01

Rework bands

through

12/31/00

Rework bands

after 12/31/00

Rework bands

after 12/31/01

Life limits

through

12/31/00

Life limits

after

12/31/00

Life limits

after

12/31/01

Life limits

through

12/31/00

Life limits

after

12/31/00

Life limits

after

12/31/01

RB.211–22B–02 Pre

SB72–5787 and

Pre SB72–8700 ... 11000 10000 9000 8000–11000 7500–10000 7500–9000 18000 17600 16600 N/A N/A N/A

RB.211–22B–02 Pre

SB72–5787 and

Post SB72–8700 .. 11000 10000 10000 8000–11000 7500–10000 7500–10000 17310 16960 15960 N/A N/A N/A

RB.211–22B–02

Post SB72–5787

and Pre SB72–

8700 ..................... 11000 11000 11000 8000–11000 8000–11000 8000–11000 18000 18000 18000 N/A N/A N/A

RB.211–22B–02

Post SB72–5787

and Post SB72–

8700 ..................... 11000 11000 11000 8000–11000 8000–11000 8000–11000 17310 17310 17310 N/A N/A N/A

RB.211–524B–02

RB.211–524B3–02

RB.211–524B4–02

Pre SB72–5787 ... 7500 7250 6250 6000–7500 4750–7250 4750–6250 13500 13500 12750 17500 17500 17500

RB.211–524B–02

RB.211–524B3–02

RB.211–524B4–02

Post SB72–5787 .. 8500 8200 7200 6500–8500 5700–8200 5700–7200 15000 14700 13700 19000 19000 18000

35816 Federal Register / Vol. 65, No. 109 / Tuesday, June 6, 2000 / Rules and Regulations

TABLE 1—Continued

Engine mark and mod

standard

Pre SB72–9594 Rework bands Post SB72–9594 Post SB72–9618

Life limits

through

12/31/00

Life limits

after

12/31/00

Life limits

after

12/31/01

Rework bands

through

12/31/00

Rework bands

after 12/31/00

Rework bands

after 12/31/01

Life limits

through

12/31/00

Life limits

after

12/31/00

Life limits

after

12/31/01

Life limits

through

12/31/00

Life limits

after

12/31/00

Life limits

after

12/31/01

RB.211–524B–B–02

RB.211–524B4–

D–02 Pre SB72–

5787 ..................... 7500 7500 7400 6000–7500 6000–7500 5500–7400 13500 13500 13500 17500 17500 17500

RB.211–524B–B–02

RB.211–524B4–

D–02 Post SB72–

5787 ..................... 8500 8200 7200 6500–8500 5700–8200 5700–7200 15000 14700 13700 19000 19000 18000

RB211–524B2

RB211–524C2

RB211–524D4

RB211–524D4X

Pre SB72–5787 ... 7500 7500 7300 6000–7500 6000–7500 5800–7300 13500 13500 13500 17500 17500 17500

RB.211–524B2

RB.211–524C2

RB.211–524D4

RB.211–524D4X

Post SB72–5787 .. 8500 8250 7250 6500–8500 5800–8250 5800–7250 15000 14500 13500 19000 18750 17750

RB.211–524B2–B

RB.211–524C2–B

Pre SB72–5787 ... 7500 7500 7300 6000–7500 6000–7500 5800–7300 13500 13500 13500 17500 17500 17500

RB.211–524B2–B

RB.211–524C2–B

Post SB72–5787 .. 8500 8200 7250 6500–8500 5800–8200 5800–7250 15000 14500 13500 19000 18650 17650

RB.211–524D4–B

RB.211–524D4X–

B Post SB72–

5787 ..................... 8500 8500 7750 6500–8500 6500–8500 5750–7750 15000 15000 15000 19000 19000 19000

RB.211–524G

RB.211–524G–T

RB.211–524H

RB.211–524H–T

Post SB72–5787 .. 8500 8150 7150 6500–8500 5750–8150 5750–7150 13950 13950 13950 N/A N/A N/A

(b) Remove from service IP stage 6–7 rotor

shafts that have been reworked in accordance

with R–R SB RB.211–72–9594, Revision 8,

dated January 14, 1999, Revision 7, dated

September 16, 1994, Revision 6, dated

August 12, 1994, or Revision 5, dated

February 12, 1993, prior to exceeding the

new, reduced cyclic life listed in Table 1 of

this AD under the sub-title ‘‘Post SB72–

9594’’ and replace with serviceable parts.

(c) Remove from service IP compressor

stage 6–7 rotor shafts that have been

reworked in accordance with R–R SB

RB.211–72–9618, dated August 7, 1992, prior

to exceeding the new, reduced cyclic life

limits listed in Table 1 of this AD under the

sub-title ‘‘Post SB72–9618’’ and replace with

serviceable parts.

(d) IP compressor stage 6–7 rotor shaft

rework in accordance with R–R SB RB.211–

72–9594 can only be accomplished when the

cyclic life of the part falls within the rework

bands established in Table 1 of this AD. To

accomplish rework of IP compressor stage 6–

7 rotor shafts prior to reaching the lower

limit of the rework bands specified in Table

1 of this AD, the part must be artificially aged

to the cyclic life which defines the lower

limit of the applicable rework bands in Table

1 of this AD.

Note 2: For example, if the lower limit of

the rework band is 8,000 cycles, and the part

is reworked at 7,000 cycles, the part must be

artificially aged by adding 1,000 cycles to the

cycles since new recorded on the part; i.e.,

on return to service the cycles since new on

this part would be 8,000 cycles.

Alternative Method 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, Engine

Certification Office. Operators shall submit

their request through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

Ferry Flights

(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 aircraft to a

location where the requirements of this AD

can be accomplished.

Incorporation By Reference

(g) The actions of this AD shall be done in

accordance with the following R–R Service

Bulletins:

Document No. Pages Revision Date

RB.211–72–9993 ................................................................ 1–6 ....................................... Original ................................. August 26, 1994.

Supplement ......................................................................... 1 of 1 .................................... Original ................................. August 26, 1994.

Modification Acceptance ..................................................... .............................................. Original ................................. August 26, 1994.

Total pages: 8

RB.211–72–9594 ................................................................ 1–4 ....................................... 8 ........................................... January 14, 1999.

4A ......................................... 8 ........................................... January 14, 1999.

5–6 ....................................... 8 ........................................... January 14, 1999.

6A ......................................... 2 ........................................... May 8, 1992.

7 ........................................... 6 ........................................... August 12, 1994.

8–8A ..................................... 8 ........................................... January 14, 1999.

9 ........................................... 2 ........................................... May 8, 1992.

10–11 ................................... 6 ........................................... August 12, 1994.

Federal Register / Vol. 65, No. 109 / Tuesday, June 6, 2000 / Rules and Regulations 35817

Document No. Pages Revision Date

12–12A ................................. 8 ........................................... January 14, 1999.

13–15 ................................... 7 ........................................... September 16, 1994.

16–18 ................................... Original ................................. February 5, 1992.

19–20 ................................... 4 ........................................... November 13, 1992.

21–26 ................................... 6 ........................................... August 12, 1994.

27 ......................................... 7 ........................................... September 16, 1994.

Appendix ............................................................................. 1–4 ....................................... 5 ........................................... February 12, 1993.

5 ........................................... Original ................................. February 5, 1992.

Supplement ......................................................................... 1–2 ....................................... 1 ........................................... August 12, 1994.

Total pages: 38

RB.211–72–9618 ................................................................ 1–6 ....................................... 2 ........................................... January 14, 1999.

Total pages: 6

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 plc, P.O. Box 31, Derby,

DE24 8BJ, UK, telephone 011–44–1332–

242424. 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.

Effective Date

(h) This amendment becomes effective on

August 7, 2000.

Issued in Burlington, Massachusetts, on

May 23, 2000.

Thomas A. Boudreau,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–13566 Filed 6–5–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–358–AD; Amendment

39–11761; AD 2000–11–13]

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 adopts a

new airworthiness directive (AD),

applicable to certain Fokker Model F.28

Mark 1000, 2000, 3000, and 4000 series

airplanes, that requires a one-time

review of the maintenance records to

determine if tripping of the fuel boost

pump circuit breakers has been

recorded, repetitive inspections to

detect fuel leakage from the fuel boost

pump wiring conduits, and corrective

actions, if necessary. This amendment

also requires replacement of the three

single wires inside the metal conduit of

the fuel boost pumps with new wires

protected by a polyamide sleeve, which

terminates the repetitive inspections.

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 the fuel boost pump

wiring from chafing, which could result

in electrical arcing and a possible fuel

tank ignition source.

DATES: Effective July 11, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 11,

2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Fokker Services B.V., P.O. Box

231, 2150 AE Nieuw-Vennep, the

Netherlands. 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 Fokker

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

4000 series airplanes was published in

the Federal Register on February 8,

2000 (65 FR 6046). That action proposed

to require a one-time review of the

maintenance records to determine if

tripping of the fuel boost pump circuit

breakers has been recorded, repetitive

inspections to detect fuel leakage from

the fuel boost pump wiring conduits,

and corrective actions, if necessary.

That action also proposed to require

replacement of the three single wires

inside the metal conduit sleeve of the

fuel boost pumps with new wires

protected by a polyamide sleeve, which

would terminate the repetitive

inspections.

Comments Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Type Certificate Holder

One commenter requests that the

Discussion and Explanation of Relevant

Service Information sections be revised

to refer to Fokker Services B.V. as the

current type certificate holder, rather

than the now defunct airplane

manufacturer. The commenter advises

that Fokker Services B.V. is conducting

the Fuel System Safety Program

mentioned in the Discussion section,

and is also the issuer of the relevant

service information. The FAA

acknowledges the accuracy of this

information; however, since these

sections are not repeated in the final

rule, no change is made to the AD.

Statement of Unsafe Condition

The same commenter requests that the

statement of unsafe condition be

corrected in several areas of the

proposed AD. The commenter notes that

electrical arcing has only been observed

between the metal conduit and the fuel

boost pump wiring, and states that the

description of the unsafe condition

should be revised to remove the

statement that such arcing ‘‘could result

in a possible fuel tank ignition source.’’

The commenter states that since no arcthrough of the metal conduit has been

observed, and the conduit is submerged

in fuel during all phases of flight, it is

very unlikely that the arcing could serve

as an ignition source for the fuel vapors

inside the fuel tank. The commenter