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

35818 Federal Register / Vol. 65, No. 109 / Tuesday, June 6, 2000 / Rules and Regulations

requests that the Summary, Discussion,

and Compliance sections of the AD be

revised to eliminate such a statement,

and suggests that the actions required by

the proposed AD are instead intended to

prevent repetitive electrical arcing

between damaged fuel boost pump

wiring and the metal conduit, ignition

of fuel vapors within the metal conduit,

and/or chafing of the fuel boost pump

wiring.

The FAA does not concur. Although

the commenter states that it is very

unlikely that the arcing could lead to an

ignition source for the fuel vapors inside

the fuel tank, insufficient data were

provided to the FAA to demonstrate that

such arcing could not create an ignition

source in the fuel tank. Additionally,

although other conditions will be

prevented by accomplishment of the

actions required by this AD, the possible

ignition of fuel vapors is the unsafe

condition being addressed by this AD.

No change is made to the final rule.

Reference to Metal Conduit

The same commenter requests that the

phrase ‘‘replacement of the three single

wires inside the metal conduit sleeve’’

in the Summary section of the proposed

AD be revised to delete the word

‘‘sleeve’’ to describe the replacement

more accurately. The FAA concurs. The

use of the word ‘‘sleeve’’ in this context

was an inadvertent error in terminology,

although the replacement is described

accurately in the text of the AD. The

Summary section of the final rule has

been revised accordingly.

Description of Service Information

The same commenter requests that the

Explanation of Relevant Service

Information section be revised in several

areas pertaining to the description of the

procedures contained in Part 2,

Paragraph D., of the Accomplishment

Instructions of Fokker Service Bulletin

SBF28/28–046, dated September 1,

1999. The commenter’s suggestions

include expanding the description of

the corrective actions to list all such

actions, and clarifying that certain

actions are to be accomplished

subsequent to and depending on the

results of the resistance check. The FAA

acknowledges that more detailed

descriptions of all corrective actions

could have been included, but has

determined that the description

provided in the proposed AD was

sufficient to give adequate notice to

operators concerning required actions.

Since this information is not retained in

the final rule, no change is made to the

AD in this regard.

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

described previously. 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 22 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 review of the maintenance

records, and that the average labor rate

is $60 per work hour. Based on these

figures, the cost impact of the review on

U.S. operators is estimated to be $1,320,

or $60 per airplane.

It will take approximately 3 work

hours per airplane to accomplish the

required repetitive inspection, at an

average labor rate of $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 $3,960,

or $180 per airplane, per inspection

cycle.

It will take approximately 33 work

hours per airplane to accomplish the

required modification, at an average

labor rate of $60 per work hour.

Required parts will cost approximately

$1,355 per airplane. Based on these

figures, the cost impact of the

modification required by this AD on

U.S. operators is estimated to be

$73,370, or $3,335 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 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:

2000–11–13 Fokker Services B.V.:

Amendment 39–11761. Docket 99–NM–

358—AD.

Applicability: Model F.28 Mark 1000,

2000, 3000, and 4000 series airplanes having

serial numbers 11003 through 11241

inclusive and 11991 through 11994 inclusive,

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 (f) 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 the fuel boost pump wiring

from chafing, which could result in electrical

arcing and a possible fuel tank ignition

source, accomplish the following:

Inspections and Corrective Actions

(a) Within 30 days after the effective date

of this AD, perform a one-time inspection of

the maintenance records of the airplane to

determine if tripping of the fuel boost pump

Federal Register / Vol. 65, No. 109 / Tuesday, June 6, 2000 / Rules and Regulations 35819

circuit breakers has been reported within the

last 30 days, in accordance with Part 1 of the

Accomplishment Instructions of Fokker

Service Bulletin SBF28/28–046, dated

September 1, 1999.

(b) If resettable or unresettable tripping of

the circuit breaker of the fuel boost pump is

reported during the inspection required by

paragraph (a) of this AD, or if such tripping

is reported at any time subsequent to that

inspection: Within 10 days after the date of

the inspection or any occurrence, accomplish

the applicable repair (including a resistance

check and inspections of the wire and

conduit for discrepancies), in accordance

with Part 2 of the Accomplishment

Instructions of Fokker Service Bulletin

SBF28/28–046, dated September 1, 1999. If

any discrepancy is detected during any

inspection performed during the repair, prior

to further flight, repair in accordance with

the service bulletin.

(c) In the event of any resettable or

unresettable tripping of the circuit breakers

of the fuel boost pump as indicated in

paragraph (b) of this AD, the airplane may be

operated for a period not to exceed 10 days

after the occurrence, provided the circuit

breaker of the fuel boost pump and fuel boost

pump switch have been properly deactivated

and placarded for flightcrew awareness, in

accordance with the FAA-approved Master

Minimum Equipment List (MMEL).

(d) Within 30 days after the effective date

of this AD, perform a general visual

inspection to detect signs of fuel leakage from

the wiring conduits of the fuel boost pumps,

in accordance with Part 1 of the

Accomplishment Instructions of Fokker

Service Bulletin F28/28–046, dated

September 1, 1999. If any fuel leakage is

detected during the inspection, prior to

further flight, isolate the fuel leak, and repair

in accordance with Part 2 of the

Accomplishment Instructions of the service

bulletin. Thereafter, repeat the inspection at

intervals not to exceed 90 days.

Note 2: For the purposes of this AD, a

general visual inspection is defined as: ‘‘A

visual examination of an interior or exterior

area, installation, or assembly to detect

obvious damage, failure, or irregularity. This

level of inspection is made under normally

available lighting conditions such as

daylight, hangar lighting, flashlight, or droplight, and may require removal or opening of

access panels or doors. Stands, ladders, or

platforms may be required to gain proximity

to the area being checked.’’

Replacement of Wires

(e) Replace the existing three single wires

(including inspections) inside the metal

conduits of the fuel boost pumps with three

twisted wires protected by a polyamide

braided wire sleeve, in accordance with Part

3 of the Accomplishment Instructions of

Fokker Service Bulletin F28/28–046, dated

September 1, 1999, at the time specified in

paragraph (e)(1) or (e)(2) of this AD, as

applicable. If any discrepancy is detected

during any inspection required by this

paragraph, prior to further flight, repair in

accordance with the service bulletin.

Accomplishment of the actions required by

this paragraph constitutes terminating action

for the actions required by this AD.

(1) For airplanes that have accumulated

less than 40,000 total flight hours as of the

effective date of this AD: Within 2 years after

the effective date of this AD.

(2) For airplanes that have accumulated

40,000 or more total flight hours as of the

effective date of this AD: Within 1 year after

the effective date of this AD.

Alternative Methods of Compliance

(f) 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.

Special Flight Permits

(g) 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.

Incorporation by Reference

(h) The actions shall be done in accordance

with Fokker Service Bulletin SBF28/28–046,

dated September 1, 1999. 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 Fokker Services B.V., P.O.

Box 231, 2150 AE Nieuw-Vennep, 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 4: The subject of this AD is addressed

in Dutch airworthiness directive BLA 1999–

114, dated September 13, 1999.

(i) This amendment becomes effective on

July 11, 2000.

Issued in Renton, Washington, on May 25,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–13694 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–SW–62–AD; Amendment

39–11766; AD 2000–11–18]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model SA–365C, C1, C2, N, and

N1; AS–365N2 and N3; and SA–366G1

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD)

that applies to Eurocopter France Model

SA–365C, C1, C2, N, and N1; AS–

365N2, and SA–366G1 helicopters. That

AD currently requires inspecting the

tightening torque of the main rotor hub

blade attach beam spherical thrust

bearing bolts (bolts) and either applying

a specified torque or, if necessary,

inspecting for a crack in the metal

components. That AD also requires

replacing the spherical thrust bearing

(bearing) with an airworthy bearing if a

crack is found. This amendment

requires the same actions as the existing

AD, but adds the Eurocopter France

Model AS–365N3 helicopter to the

applicability. This amendment is

prompted by reports of cracks in the

metal components of the bearing

attachment joint and the need to add the

Eurocopter France Model AS–365N3

helicopter to the applicability. The

actions specified by this AD are

intended to prevent loosening of bearing

bolts in flight, which may cause cracks

in the metal components, failure of the

bearing, and subsequent loss of control

of the helicopter.

EFFECTIVE DATE: July 11, 2000.

FOR FURTHER INFORMATION CONTACT: Paul

Madej, Aviation Safety Engineer, FAA,

Rotorcraft Directorate, Regulations

Group, 2601 Meacham Blvd., Fort

Worth, Texas 76137, telephone (817)

222–5125, fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 99–21–24,

Amendment 39–11369 (64 FR 55621,

October 14, 1999), which applies to

Eurocopter France Model SA–365C, C1,

C2, N, and N1; AS–365N2, and SA–

366G1 helicopters, was published in the

Federal Register on February 29, 2000

(65 FR 10727). That action proposed to

require requires the same actions as the

existing AD, but adds the Eurocopter