[Federal Register Volume 62, Number 236 (Tuesday, December 9, 1997)]
[Proposed Rules]
[Pages 64775-64777]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-32113]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-248-AD]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F28 Mark 0070 and Mark
0100 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 Fokker Model F28 Mark 0070 and
Mark 0100 series airplanes. This proposal would require inspection of
the wing leading edge sections for the correct amount of bleed air
exhaust holes, and corrective actions, if necessary. This proposal is
prompted by issuance of mandatory continuing airworthiness information
by a foreign civil airworthiness authority. The actions specified by
the proposed AD are intended to prevent malfunction of the wing leading
edge thermal anti-ice system, which could result in reduced
controllability of the airplane and/or reduced structural integrity of
the wing due to overheating.
DATES: Comments must be received by January 8, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 97-NM-248-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from Fokker Services B.V., Technical Support Department, P.O.
Box 75047, 1117 ZN Schiphol Airport, the Netherlands. This information
may be examined at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington.
FOR FURTHER INFORMATION CONTACT: 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:
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 notice may be changed in
light of the comments received.
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 notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 97-NM-248-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-103, Attention: Rules
Docket No. 97-NM-248-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Rijksluchtvaartdienst (RLD), which is the airworthiness
authority for the Netherlands, notified the FAA that an unsafe
condition may exist on all Fokker Model F28 Mark 0070 and Mark 0100
series airplanes. The RLD advises that, during assembly of a Fokker
Model F28 Mark 0100 series airplane, it was discovered that the number
of bleed air exhaust holes in one of the wing leading edge sections was
not in conformity with type design. Subsequent investigation revealed
that some spare wing leading edge sections did not have any bleed air
exhaust holes present.
[[Page 64776]]
Missing bleed air exhaust holes may cause improper bleed air
circulation within the wing thermal anti-ice system. This condition, if
not corrected, could result in malfunction of the wing leading edge
thermal anti-ice system, which could result in reduced controllability
of the airplane and/or reduced structural integrity of the wing due to
overheating.
Explanation of Relevant Service Information
Fokker has issued Service Bulletin SBF100-57-032, dated August 21,
1995, which describes procedures for a one-time visual inspection of
the wing leading edge sections for the correct amount of bleed air
exhaust holes, and rework of the wing leading edge sections to add the
correct amount of holes, if necessary. The service bulletin also
describes procedures for visual inspection of the adjacent structure of
certain wing leading edge sections to detect heat damage, and repair,
if necessary. The service bulletin references Fokker Component Service
Bulletin D14000-57-004, dated August 21, 1995, as an additional sources
of service information for a one-time visual inspection of the wing
leading edge sections held in spares for the correct amount of bleed
air exhaust holes, and rework of the wing leading edge sections to add
the correct amount of holes, if necessary. Accomplishment of the
actions specified in the service bulletins is intended to adequately
address the identified unsafe condition. The RLD classified these
service bulletins as mandatory and issued Dutch airworthiness directive
BLA No. 1995-087 (A), dated August 31, 1995, in order to assure the
continued airworthiness of these airplanes in the Netherlands.
FAA's Conclusions
These airplane models are manufactured in the Netherlands and are
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 RLD has kept the FAA
informed of the situation described above. The FAA has examined the
findings of the RLD, 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 bulletins described previously,
except as discussed below.
Differences Between Proposed Rule and Service Bulletin
Fokker Service Bulletin SBF100-57-032, dated August 21, 1995,
specifies that operators are to contact the manufacturer for repair
instructions if any heat damage is found. However, this proposed AD
would require that the repairs be accomplished in accordance with a
method approved by the FAA.
Cost Impact
The FAA estimates that 131 Fokker Model F28 Mark 0070 and Mark 0100
series 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 inspection on U.S. operators is estimated to be $7,860, or $60
per airplane.
The cost impact figure discussed above is based on assumptions 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 AD were not adopted.
Regulatory Impact
The regulations proposed herein would not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
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: Docket 97-NM-248-AD.
Applicability: All Model F28 Mark 0070 and Mark 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
otherwise 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 (c) 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 malfunction of the wing leading edge thermal anti-ice
system, which could result in reduced controllability of the
airplane and/or reduced structural integrity of the wing due to
overheating, accomplish the following:
(a) Within 60 days after the effective date of this AD, inspect
all wing leading edge sections for the presence of the correct
number of bleed air exhaust holes, in accordance with Part 1 of the
Accomplishment Instructions of Fokker Service Bulletin SBF100-57-
032, dated August 21, 1995. If any missing holes are detected, prior
to further flight, accomplish paragraph (a)(1) and (a)(2) of this
AD, in accordance with Part 2 of the Accomplishment Instructions of
the service bulletin:
[[Page 64777]]
(1) Rework the affected wing leading edge section(s) to add the
correct number of holes, and
(2) Perform a visual inspection of the auxiliary spar or front
spar, as applicable, to detect heat damage. If any heat damage is
detected, prior to further flight, repair the affected structure in
accordance with a method approved by the Manager, International
Branch, ANM-116, FAA, Transport Airplane Directorate.
(b) As of the effective date of this AD, no person shall install
a wing leading edge section, unless it has been inspected for the
presence of the correct number of bleed air exhaust holes, and
reworked, if necessary, to add the correct number of holes, in
accordance with Fokker Component Service Bulletin D14000-57-004,
dated August 21, 1995.
(c) 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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(d) 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 3: The subject of this AD is addressed in Dutch
airworthiness directive BLA No. 1995-087 (A), dated August 31, 1995.
Issued in Renton, Washington, on December 2, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-32113 Filed 12-8-97; 8:45 am]
BILLING CODE 4910-13-U