[Federal Register: March 4, 2003 (Volume 68, Number 42)]
[Rules and Regulations]
[Page 10154-10156]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr04mr03-6]
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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]
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