[Federal Register Volume 62, Number 104 (Friday, May 30, 1997)]
[Proposed Rules]
[Pages 29308-29309]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-14183]
[[Page 29308]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-174-AD]
RIN 2120-AA64
Airworthiness Directives; Fokker F28 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 Fokker Model F28 Mark 1000,
2000, 3000, and 4000 series airplanes. This proposal would require a
one-time visual inspection of the rear cargo door and luggage auxiliary
structure for corrosion, repetitive borescope inspections of the rear
cargo door, and removal and repair of any corrosion found during the
inspections. This proposal would also require the drilling of drain
holes and application of a corrosion preventive and sealing compound
inside the rear cargo door, and modification of the rear cargo door to
aid in future routine borescope inspections. This proposal is prompted
by reports of corrosion being found in the affected areas on several of
the affected airplanes. The actions specified by the proposed AD are
intended to prevent such corrosion, which could result in structural
failure of the cargo door and loss of the door during flight, and
consequent rapid decompression, aerodynamic instability, and/or damage
to other fuselage structures.
DATES: Comments must be received by July 11, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 96-NM-174-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 Aircraft USA, Inc., 1199 North Fairfax Street,
Alexandria, Virginia 22314. This information may be examined at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington.
FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2141; 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 96-NM-174-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. 96-NM-174-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 F28 Mark 1000, 2000, 3000, and 4000
series airplanes. The RLD advises that corrosion has been found inside
the rear cargo door during the replacement of the door hinge on several
of the affected airplanes. In one instance, corrosion was so severe
that a number of parts required replacement. The location of the rear
cargo door is such that toilet fluids may enter the door, and the
insulation blankets may absorb these fluids, which could cause a
continuous corrosive environment inside the door. This condition, if
not detected and corrected in a timely manner, could result in
structural failure of the cargo door and loss of the door during
flight, which could result in rapid decompression, aerodynamic
instability, and/or damage to other fuselage structures.
Explanation of Relevant Service Information
Fokker has issued Service Bulletin F28-52-111, dated March 12,
1994, which describes procedures for the following:
--A one-time visual inspection of the rear cargo door and auxiliary
structure for corrosion;
--Removal and repair of any corrosion;
--Drilling drain holes and applying a corrosion preventive and sealing
compound inside the rear cargo door; and
--Modification of the rear cargo door to provide inspection holes for
borescope inspections.
The RLD classified this service bulletin as mandatory and issued
Dutch airworthiness directive BLA No. 1995-126 (A), dated November 30,
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 a one-time visual
inspection of the rear cargo door and luggage auxiliary structure for
corrosion, repetitive borescope inspections of the rear cargo door, and
removal and repair of any corrosion found during the inspections.
[[Page 29309]]
This proposed AD would also require the drilling of drain holes and
application of a corrosion preventive and sealing compound inside the
rear cargo door, and modification of the rear cargo door to aid in the
future routine borescope inspections. The actions would be required to
be accomplished in accordance with the service bulletin described
previously, except for the repetitive borescope inspections and follow-
on actions, which would be required to be accomplished in accordance
with the F28 Maintenance Manual.
Cost Impact
The FAA estimates that 37 airplanes of U.S. registry would be
affected by this proposed AD.
It would take approximately 13 work hours per airplane to
accomplish the proposed initial inspection, at an average labor rate of
$60 per work hour. The FAA has no way of determining how many
repetitive inspections the owners/operators would incur over the life
of the affected airplanes. Based on these figures, the cost impact of
the initial inspection proposed by this AD on U.S. operators is
estimated to be $28,860, or $780 per airplane.
It would take approximately 27 work hours per airplane to
accomplish the proposed modification, at an average labor rate of $60
per work hour. Required parts would be supplied by the manufacturer at
no cost to the operators. Based on these figures, the cost impact of
the modification proposed by this AD on U.S. operators is estimated to
be $59,940, or $1,620 per airplane.
The cost impact figures discussed above are 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 96-NM-174-AD.
Applicability: All F28 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
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 corrosion in the rear cargo door, which could result
in structural failure of the cargo door and loss of the door during
flight, and consequent rapid decompression, aerodynamic instability,
and/or damage to other fuselage structures, accomplish the
following:
(a) Within 2 years after the effective date of this AD,
accomplish the requirements of paragraphs (a)(1), (a)(2), and (a)(3)
of this AD, in accordance with Fokker Service Bulletin F28-52-111,
dated March 12, 1994.
(1) Perform a one-time visual inspection of the rear cargo door
and luggage auxiliary structure for corrosion. If any corrosion is
found, prior to further flight, remove and repair it.
(2) Drill drain holes and apply a corrosion preventive and
sealing compound inside the rear cargo door.
(3) Modify the rear cargo door to provide inspection holes for
borescope inspections.
(b) Within 6,000 hours time-in-service (TIS) or 3 years after
accomplishing the visual inspection required by paragraph (a)(1) of
this AD, whichever occurs first; and thereafter at intervals not to
exceed 6,000 hours TIS or 3 years, whichever occurs first: Perform a
borescope inspection of the rear cargo door for corrosion in
accordance with Chapter 52-30-2 of the F28 Maintenance Manual. If
any corrosion is detected, prior to further flight, remove and
repair it in accordance with the maintenance manual.
(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, Standardization Branch, ANM-113,
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,
Standardization Branch, ANM-113.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(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. Issued in Renton,
Washington, on May 23, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-14183 Filed 5-29-97; 8:45 am]
BILLING CODE 4910-13-P
