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

[Federal Register Volume 68, Number 42 (Tuesday, March 4, 2003)]
[Rules and Regulations]
[Pages 10154-10156]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-4165]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-334-AD; Amendment 39-13057; AD 2003-04-09]
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 all Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 
series airplanes, that requires repetitive inspections for 
discrepancies of the internal fuselage skin panels located in the stub 
wing areas; and corrective action if necessary. This action is 
necessary to detect and correct heat damage to the fuselage skin panels 
caused by the leakage of hot air from one of the bleed air ducts inside 
the stub wing, which could result in reduced structural integrity of 
the engine support structure. This action is intended to address the 
identified unsafe condition.

DATES: Effective April 8, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 8, 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 1000, 
2000, 3000, and 4000 series airplanes was published in the Federal 
Register on November 21, 2002 (67 FR 70189). That action proposed to 
require repetitive inspections for discrepancies of the internal 
fuselage skin panels located in the stub wing areas; and corrective 
action if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Interim Action

    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.

Cost Impact

    The FAA estimates that 24 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 1 work hour per 
airplane to accomplish the proposed 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 $1,440, or 
$60 per airplane, per inspection cycle.
    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

[[Page 10155]]

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--09  Fokker Services B.V.: Amendment 39-13057. Docket 2001-
NM-334-AD.
    Applicability: All Model F.28 Mark 1000, 2000, 3000, and 4000 
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 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 detect and correct heat damage to the fuselage skin panels 
caused by the leakage of hot air from one of the bleed air ducts 
inside the stub wing, and consequent reduced structural integrity of 
the engine support structure; accomplish the following:

Repetitive Inspections

    (a) Within 6,000 flight cycles after the effective date of this 
AD: Perform a general visual inspection of the internal fuselage 
structure between frames 16060 and 16660 and the beams at the upper 
and lower stub wing angles in the stub wing (engine pylon) areas, 
for discoloration of the primer paint, buckling or waviness of the 
skin panel, loose and/or missing fasteners, or fasteners with 
sheared-off heads, by accomplishing all actions specified in Part 1 
of the Accomplishment Instructions of Fokker Service Bulletin F28/
53-151, dated June 4, 2001. Repeat the inspection at intervals not 
to exceed 6,000 flight cycles.

    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 from within 
touching distance unless otherwise specified. A mirror may be 
necessary to enhance visual access to all exposed surfaces in the 
inspection area. 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.''

Corrective Actions

    (b) Except as provided by paragraph (c) of this AD, if any 
discrepancy is found (i.e., primer paint discoloration; buckling or 
waviness of the skin panel; missing, damaged, or loose rivets) 
during the general visual inspection required by paragraph (a) of 
this AD, before further flight, perform the applicable follow-on 
corrective actions (e.g., eddy current inspection; measurement of 
the length and depth of buckles or waves in the skin panel; repair 
of skin panels with heat damage, buckling, or waviness that are not 
within the acceptable limits specified in the service bulletin, or 
replacement with new skin panels; and replacement of loose and/or 
missing fasteners, or fasteners having sheared-off heads with new 
fasteners; as applicable) specified in the Accomplishment 
Instructions of Fokker Service Bulletin F28/53-151, dated June 4, 
2001.
    (c) If buckling or waviness of the skin panel is detected during 
the general visual inspection required by paragraph (a) of this AD, 
and the depth is within the limits specified in Part 2, paragraph 
C.(2) of the Accomplishment Instructions of Fokker Service Bulletin 
F28/53-151, dated June 4, 2001, the affected area must be repaired 
within 2,000 flight cycles after accomplishment of the inspection 
required by paragraph (a) of this AD.
    (d) Repair or replacement of damaged fuselage skin panels or 
fasteners does not terminate the repetitive inspections required by 
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, 
Transport Airplane Directorate, FAA. 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 Services B.V.

[[Page 10156]]

Service Bulletin F28/53-151, dated June 4, 2001, excluding Manual 
Change Notification--Maintenance Documentation MCNM F28-025, dated 
June 4, 2001. 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 2001-093, dated July 31, 2001.

Effective Date

    (h) This amendment becomes effective on April 8, 2003.

    Issued in Renton, Washington, on February 13, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-4165 Filed 3-3-03; 8:45 am]
BILLING CODE 4910-13-P

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