[Federal Register Volume 65, Number 109 (Tuesday, June 6, 2000)]
[Rules and Regulations]
[Pages 35817-35819]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-13694]


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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.

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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 arc-through 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

[[Page 35818]]

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.


Sec. 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

[[Page 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 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.''

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 
Secs. 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]
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