[Federal Register Volume 68, Number 40 (Friday, February 28, 2003)]
[Rules and Regulations]
[Pages 9511-9513]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-4348]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-289-AD; Amendment 39-13068; AD 2003-04-19]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 
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 all Fokker Model F.28 Mark 0070 and 0100 series 
airplanes, that requires a one-time general visual inspection to detect 
any missing attachment bolts in the replaceable frame struts, and 
corrective actions, if necessary. This action is necessary to prevent 
excessive deformation of the floor structure in the event of rapid 
decompression in the lower cargo hold due to missing attachment bolts 
in the replaceable frame struts. Such deformation may result in the 
flight and engine control cables becoming jammed, and consequent 
reduced controllability of the airplane. This action is intended to 
address the identified unsafe condition.

DATES: Effective April 4, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 4, 2003.

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: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1137; 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 all Fokker Model F.28 Mark 0070 
and 0100 series airplanes was published in the Federal Register on 
March 28, 2002 (67 FR 14891). That action proposed to require a one-
time general visual inspection to detect any missing attachment bolts 
in the replaceable frame struts, and corrective actions, if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for the Proposed Rule

    One commenter supports the proposed rule.

Request To Reference Latest Service Information

    One commenter requests that Revision 1 to Fokker Service Bulletin 
SBF100-53-096 be cited as an acceptable source of service information 
for compliance with the proposed AD. That revision adds two figures to 
the service bulletin that are applicable to the operator's fleet.
    The commenter also states that it notified the manufacturer of 
typographical errors in Figures 2 and 17 of the service bulletin. The 
manufacturer informed the commenter that a Service Bulletin Change 
Notification (SBCN) to correct the typographical errors would be 
issued. The commenter requests that a statement allowing the use of 
future service bulletin revisions and SBCNs be included in the proposed 
AD.
    The FAA concurs with the commenter's request to reference Revision 
1 of the service bulletin and the applicable SBCN. Since the issuance 
of the proposed AD, the manufacturer has issued Fokker Service Bulletin 
SBF100-53-096, Revision 1, dated November 22, 2001; and Fokker SBCN 
SBF100-53-096/02, dated January 28, 2002. The proposed rule references 
the original issue of the service bulletin, dated April 11, 2001, as 
the appropriate

[[Page 9512]]

source of service information for accomplishment of the proposed 
inspection. The actions in Revision 1 are essentially similar to those 
in the original issue of the service bulletin. The SBCN corrects 
typographical errors to part numbers in Figures 2 and 17 of the service 
bulletin. Part number NAS694V6 in Figure 2 has been changed to 
NAS674V6. Part number NAS695V10 in Figure 17 has been changed to 
NAS675V10. The manufacturer notified the FAA that bolts having part 
numbers NAS694V6 and NAS695V10 do not exist.
    We have revised paragraph (a) of the final rule to reference 
Revision 1 of the service bulletin, including SBCN SBF100-53-096/02 as 
the appropriate source of service information. We have also included 
new paragraphs (b) and (d) in this final rule (and re-lettered other 
paragraphs accordingly) to give credit for inspections and corrective 
actions accomplished before the effective date of this AD per the 
original issue of the service bulletin.

Request To Include Alternative Methods of Compliance

    One commenter requests that the proposed AD include a statement 
allowing the use of alternate and interchangeable fasteners approved by 
Fokker. The commenter states that Fokker Message TS01.60550, dated 
November 29, 2001, indicates approval from Fokker Services to use 
interchangeable parts. In regard to the commenter's fleet, the service 
bulletin lists parts that are inactive and have an interchangeable list 
or an alternate parts list.
    The FAA does not concur with this comment. Paragraph (c)(2) of the 
final rule allows operators to make repairs per a method approved by 
either the FAA or the Civil Aviation Authority--The Netherlands (CAA-
NL) (or its delegated agent). If an operator wants to make a repair 
using a part other than the one specified in the service bulletin, that 
paragraph allows the operator to contact the FAA or CAA-NL (or its 
delegated agent) for approval.

Request To Revise Cost Impact

    One commenter states that it has begun inspections of the affected 
aircraft in accordance with Fokker Service Bulletin SBF100-53-096, 
Revision 1, dated November 22, 2001. Based on this commenter's 
experience, 12 work hours per airplane are required to accomplish the 
inspections.
    From this comment the FAA infers that the commenter is requesting 
that the Cost Impact section of the proposed AD be revised. The FAA 
does not concur. The cost impact information describes only the 
``direct'' costs of the general one-time visual inspection required by 
the proposed AD. The number of work hours necessary to accomplish the 
required general visual inspection, specified as 1 work hour in the 
cost impact information, was provided to the FAA by the manufacturer 
based on the best data available to date. The economic analysis of the 
AD is limited only to the cost of actions actually required by the 
rule. It does not consider the costs of ``on condition'' actions 
required if, during the one-time general visual inspection required by 
the proposed AD, any attachment bolts are found missing. The ``on 
condition'' actions include additional general visual inspections to 
detect deformations or cracks in the affected floor beams and the 
fuselage frame C-channels at the strut attachment. Such ``on-
condition'' corrective actions would be required to be accomplished, 
regardless of AD direction, in order to correct an unsafe condition 
identified in an airplane and to ensure operation of the airplane in an 
airworthy condition, as required by the Federal Aviation Regulations.

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 changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 139 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 inspection, and that the average 
labor rate is $60 per work hour. Based on these figures, the cost 
impact of the AD on U.S. operators is estimated to be $8,340, or $60 
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. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

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:

2003-04-19 Fokker Services B.V.: Amendment 39-13068. Docket 2001-NM-
289-AD.

    Applicability: All Model F.28 Mark 0070 and 0100 series 
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 
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

[[Page 9513]]

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 accomplished 
previously.
    To prevent excessive deformation of the floor structure to the 
extent that flight and engine control cables might jam, accomplish 
the following:

Inspection

    (a) Within 14 months after the effective date of this AD, do a 
one-time general visual inspection to detect any missing attachment 
bolts in the replaceable frame struts per Part 1, Part 2, and Part 3 
of the Accomplishment Instructions of Fokker Service Bulletin 
SBF100-53-096, Revision 1, dated November 22, 2001, including Fokker 
Service Bulletin Change Notification SBF100-53-096/02, dated January 
28, 2002; as applicable.
    (b) Inspections accomplished prior to the effective date of this 
AD per Fokker Service Bulletin SBF100-53-096, original issue, dated 
April 11, 2001, are acceptable for compliance with the requirements 
of paragraph (a) of this AD.

Corrective Actions

    (c) If any attachment bolts are found missing during the 
inspection required by paragraph (a) of this AD, before further 
flight, do the actions specified in paragraphs (c)(1) and (c)(2) of 
this AD.
    (1) Drill a new hole and install a new bolt (including nut and 
washer), per the Accomplishment Instructions of Fokker Service 
Bulletin SBF100-53-096, Revision 1, dated November 22, 2001, 
including Fokker Service Bulletin Change Notification SBF100-53-096/
02, dated January 28, 2002.
    (2) Do a general visual inspection to detect any deformation or 
crack in the affected floor beams and the fuselage frame C-channel 
at the strut attachment. If any deformation or crack exists, before 
further flight, repair per a method approved by either the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate; 
or the Civil Aviation Authority--The Netherlands (CAA-NL) (or its 
delegated agent).

    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.''

    (d) Corrective actions accomplished prior to the effective date 
of this AD per Fokker Service Bulletin SBF100-53-096, original 
issue, dated April 11, 2001, are acceptable for compliance with the 
requirements of paragraphs (c)(1) and (c)(2) of this AD.

Alternative Methods 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, 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

    (f) 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.

Incorporation by Reference

    (g) Unless otherwise specified in this AD, the actions shall be 
done in accordance with Fokker Service Bulletin SBF100-53-096, 
Revision 1, dated November 22, 2001, including Fokker Service 
Bulletin Change Notification SBF100-53-096/02, dated January 28, 
2002. Fokker Service Bulletin SBF100-53-096, Revision 1, contains 
the following list of effective pages:

------------------------------------------------------------------------
                                Revision level
          Page Nos.             shown on page      Date shown on page
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1, 2, 7, 8, 10, 27-30........  1..............  November 22, 2001.
3-6, 9, 11-26................  Original.......  April 11, 2001.
------------------------------
      Fokker Service Bulletin Change Notification SBF100-53-096/02
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1, 3.........................  Original.......  January 28, 2002.
2............................  Original.......  July 1, 2001.
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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 2001-055, dated April 27, 2001.

Effective Date

    (h) This amendment becomes effective on April 4, 2003.

    Issued in Renton, Washington, on February 19, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-4348 Filed 2-27-03; 8:45 am]
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