[Federal Register Volume 65, Number 26 (Tuesday, February 8, 2000)]
[Proposed Rules]
[Pages 6046-6048]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-2830]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-358-AD]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F.28 Mark 1000, 2000, 
3000, and 4000 Series Airplanes

AGENCY:  Federal Aviation Administration, DOT.

ACTION:  Notice of proposed rulemaking (NPRM).

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SUMMARY:  This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Fokker Model F.28 Mark 
1000, 2000, 3000, and 4000 series airplanes. This proposal would 
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. This proposal 
also would 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. This proposal is prompted by issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The actions specified by the proposed 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:  Comments must be received by March 9, 2000.

ADDRESSES:  Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-358-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays.
    The service information referenced in the proposed rule 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 FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 99-NM-358-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 99-NM-358-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Rijksluchtvaartdienst (RLD), which is the airworthiness 
authority for the Netherlands, notified the FAA that an unsafe 
condition may exist on certain Fokker Model F.28 Mark 1000, 2000, 3000, 
and 4000 series airplanes. On July 17, 1996, a Boeing Model 747 series 
airplane was involved in an accident shortly after takeoff from John F. 
Kennedy International Airport in Jamaica, New York. Subsequent to the 
accident, the RLD advises that the manufacturer has conducted a Fuel 
System Safety Program (FSSP) investigation. This investigation revealed 
that, on an F.28 ``Fellowship'' series airplane, the wiring insulation 
layers of the fuel boost pumps can be damaged during removal and 
installation of the wiring, or by chafing within the conduits. 
Additionally, two separate incidents of arcing have been found in the 
metal conduits of the wiring of the fuel boost pumps. Circumferential 
cracks were found in the insulation layering of the fuel boost pump 
wiring. In some cases, the cracks extended down to the conductor of the 
wiring. This condition, if not corrected, could result in electrical 
arcing and a possible fuel tank ignition source.

Explanation of Relevant Service Information

    The manufacturer has issued Fokker Service Bulletin SBF28/28-046, 
dated September 1, 1999, which describes procedures for the following:
    <bullet> Part 1 of the Accomplishment Instructions: A one-time 
review of the maintenance records to determine if tripping of the fuel 
boost pump circuit breakers has been reported, and repetitive visual 
inspections to detect fuel leakage of the fuel boost pumps.
    <bullet> Part 2, paragraph D., of the Accomplishment Instructions: 
Corrective actions for tripping of the fuel boost pump circuit 
breakers. These actions involve performing a resistance check of the 
wiring, and, if necessary, installing a new or serviceable fuel boost 
pump and correcting any system problems between the circuit breaker and 
the main landing gear (MLG) wheel bay connector, and repairing any fuel

[[Page 6047]]

leak in the metal conduit of the fuel boost pump. The corrective 
actions also involve performing one-time inspections (visual and 
boroscopic) to detect discrepancies (i.e., arcing, chafing, and 
cracking) of the insulation layers of the wiring and wiring conduits, 
and replacing the wiring and repairing the wiring conduits.
    <bullet> Part 2, paragraph E., of the Accomplishment Instructions: 
Corrective actions in the event that fuel leakage is detected from the 
fuel boost pump wiring conduits. The corrective actions involve 
inspecting the pressure bung for serviceability, and, if necessary, 
installing a new or serviceable pressure bung. Additionally, the 
corrective actions involve inspecting (visual and boroscopic) to detect 
discrepancies (i.e., arcing, chafing, and cracking) of the insulation 
layers of the wiring and wiring conduits, and replacing the wiring and 
repairing the wiring conduits.
    <bullet> Part 3 of the Accomplishment Instructions: Replacement of 
the three single wires inside the metal conduit sleeve of the fuel 
boost pump with new wires protected by a polyamide sleeve. The 
replacement also involves performing a visual inspection, and, if 
necessary, a boroscopic inspection of the boost pump wiring to detect 
discrepancies (i.e., arcing, chafing, and cracking) of the insulation 
layers of the wiring and wiring conduits, and replacing the wiring and 
repairing the wiring conduits. Accomplishment of the replacement 
eliminates the need for the repetitive inspections.
    Accomplishment of the actions specified in the service bulletin is 
intended to adequately address the identified unsafe condition. The RLD 
classified this service bulletin as mandatory and issued Dutch 
airworthiness directive BLA 1999-114, dated September 13, 1999, in 
order to assure the continued airworthiness of these airplanes in the 
Netherlands.

FAA's Conclusions

    This airplane model is manufactured in the Netherlands and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the RLD has kept the FAA informed of 
the situation described above. The FAA has examined the findings of the 
RLD, reviewed all available information, and determined that AD action 
is necessary for products of this type design that are certificated for 
operation in the United States.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, the proposed AD would require accomplishment of 
the actions specified in the service bulletin described previously.

Cost Impact

    The FAA estimates that 22 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 1 work 
hour per airplane to accomplish the proposed 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 proposed by this AD on 
U.S. operators is estimated to be $1,320, or $60 per airplane.
    It would take approximately 3 work hours per airplane to accomplish 
the proposed repetitive inspection, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of the proposed 
inspection by this AD on U.S. operators is estimated to be $3,960, or 
$180 per airplane, per inspection cycle.
    It would take approximately 33 work hours per airplane to 
accomplish the proposed modification, at an average labor rate of $60 
per work hour. Required parts would cost approximately $1,355 per 
airplane. Based on these figures, the cost impact of the proposed 
modification 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 proposed 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 proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 draft 
regulatory 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, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

Fokker Services B.V: 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:
    (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

[[Page 6048]]

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 drop-light, 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.''

    (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 
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.

    Note 4:  The subject of this AD is addressed in Dutch 
airworthiness directive BLA 1999-114, dated September 13, 1999.


    Issued in Renton, Washington, on February 2, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-2830 Filed 2-7-00; 8:45 am]
BILLING CODE 4910-13-P