[Federal Register: November 21, 2002 (Volume 67, Number 225)]
[Proposed Rules]
[Page 70189-70191]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr21no02-33]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-334-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 all
[[Page 70190]]
Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes.
This proposal would require 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: Comments must be received by December 23, 2002.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2001-NM-334-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays. Comments may be submitted via fax to (425) 227-1232.
Comments may also be sent via the Internet using the following address:
9-anm-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2001-NM-334-AD'' in the subject line and need not
be submitted in triplicate. Comments sent via the Internet as attached
electronic files must be formatted in Microsoft Word 97 for Windows or
ASCII text.
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: 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:
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 action may be changed in
light of the comments received.
Submit comments using the following format:
[sbull] Organize comments issue-by-issue. For example, discuss a
request to change the compliance time and a request to change the
service bulletin reference as two separate issues.
[sbull] For each issue, state what specific change to the proposed
AD is being requested.
[sbull] Include justification (e.g., reasons or data) for each
request.
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 action must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2001-NM-334-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. 2001-NM-334-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Civil Aviation Authority--The Netherlands (CAA-NL), which is
the airworthiness authority for the Netherlands, notified the FAA that
an unsafe condition may exist on all Fokker Model F.28 Mark 1000, 2000,
3000, and 4000 series airplanes. The CAA-NL advises that it has
received reports of heat damage to the internal fuselage skin panels
located in the stub wing areas. The cause of the heat damage was the
leakage of hot air from one of the bleed air ducts inside the stub
wing. Evidence of the heat damage was yellow discoloration of the
primer paint on the inside of the fuselage. This condition, if not
corrected, could result in reduced structural integrity of the engine
support structure.
Explanation of Relevant Service Information
Fokker Services B.V. has issued Service Bulletin F28/53-151, dated
June 4, 2001. The service bulletin describes procedures for repetitive
visual inspections of the internal fuselage skin panels in the stub
wing areas to detect discoloration of the primer paint due to heat
damage, buckling or waviness of the skin panel, loose or missing
fasteners, or fasteners with sheared-off heads; and corrective actions
if necessary. The corrective actions include an eddy current
inspection; measurement of the length and depth of buckles or waves in
the skin panel; repair or replacement of skin panels with heat damage,
buckling, or waviness that are not within the acceptable limits
specified in the service bulletin; and replacement of loose and/or
missing fasteners, or fasteners having sheared-off heads, with new
fasteners. The CAA-NL classified this service bulletin as mandatory and
issued Dutch airworthiness directive 2001-093, dated July 31, 2001, 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 CAA-NL has kept the FAA informed
of the situation described above. The FAA has examined the findings of
the CAA-NL, 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.
Interim Action
This is considered to be an interim action until a final action is
identified, at which time the FAA may consider further rulemaking.
[[Page 70191]]
Cost Impact
The FAA estimates that 24 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 inspection, and that the
average labor rate is $60 per work hour. Based on these figures, the
cost impact of the proposed 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 the assumption
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 proposed 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 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 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.
Note 4: The subject of this AD is addressed in Dutch
airworthiness directive 2001-093, dated July 31, 2001.
Issued in Renton, Washington, on November 15, 2002.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 02-29678 Filed 11-20-02; 8:45 am]
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