[Federal Register Volume 60, Number 138 (Wednesday, July 19, 1995)]
[Proposed Rules]
[Pages 37038-37040]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-17707]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-249-AD]
Airworthiness Directives; Fokker Model F28 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 certain Fokker Model F28 Mark 0100
series airplanes. For certain airplanes, this proposal would require an
inspection to determine the torque value of the attaching parts of the
interlock mechanism of the large cargo doors, and adjustment of the
torque values that are outside certain limits. For certain other
airplanes, the proposed AD would require removal of a spring from the
interlock mechanism of the large cargo doors, and installation of a new
microswitch bracket and two new springs in the interlock mechanism.
This proposal is prompted by a report indicating that a spring on the
interlock lever of the large cargo doors may become disconnected or the
lever may become jammed in the ``activated'' state. The actions
specified by the proposed AD are intended to prevent the spring from
becoming disconnected or the lever from jamming. If other failures
occur, the flightcrew could dispatch the airplane with improperly
locked cargo doors; this condition could result in the opening and/or
separation of the cargo doors while the airplane is in flight and
subsequent rapid decompression and/or structural damage to the
airplane.
DATES: Comments must be received by August 28, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-249-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
[[Page 37039]]
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 (206)
227-2141; fax (206) 227-1320.
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 94-NM-249-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. 94-NM-249-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Rijksluchtvaartdienst (RLD), which is the airworthiness
authority for the Netherlands, recently notified the FAA that an unsafe
condition may exist on certain Fokker Model F28 Mark 0100 series
airplanes. The RLD advises that a spring on the interlock lever of the
large cargo doors on these airplanes may become disconnected and/or the
lever itself may become jammed in the ``activated'' state on these
airplanes. If more failures occur when either of these situations
exist, the flightcrew will not receive a warning and could dispatch the
airplane with improperly locked cargo doors. This condition, if not
corrected, could result in the opening and/or separation of the cargo
doors while the airplane is in flight and subsequent rapid
decompression and/or structural damage to the airplane.
Fokker has issued Service Bulletin SBF100-52-045, dated August 25,
1993. For certain airplanes, the service bulletin describes procedures
for a one-time inspection to determine the torque value of the
attaching parts of the interlock mechanism of the large cargo doors,
and adjustment of the torque values that are outside certain limits.
For certain other airplanes, the service bulletin describes procedures
for removing the spring from the interlock mechanism, and installing a
new microswitch bracket and two new springs in the interlock mechanism.
The RLD classified this service bulletin as mandatory and issued Dutch
airworthiness directive BLA 93-124 (A), dated September 17, 1993, in
order to assure the continued airworthiness of these airplanes in the
Netherlands.
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 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.
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, for certain airplanes, the proposed AD would
require an inspection to determine the torque value of the attaching
parts of the interlock mechanism of the large cargo doors, and
adjustment of the torque values that are outside certain limits. For
certain other airplanes, the proposed AD would require removal of the
spring from the interlock mechanism, and installation of a new
microswitch bracket and new springs in the interlock mechanism. The
actions would be required to be accomplished in accordance with the
service bulletin described previously.
As a result of recent communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
points out that all airplanes identified in the applicability provision
of an AD are legally subject to the AD. If an airplane has been altered
or repaired in the affected area in such a way as to affect compliance
with the AD, the owner or operator is required to obtain FAA approval
for an alternative method of compliance with the AD, in accordance with
the paragraph of each AD that provides for such approvals. A note has
been included in this notice to clarify this long-standing requirement.
The FAA estimates that 61 airplanes of U.S. registry would be
affected by this proposed AD.
For 7 of these airplanes, it would take approximately 6 work hours
per airplane to accomplish the proposed inspection, at an average labor
rate of $60 per work hour. Based on these figures, the total cost
impact of the inspection proposed by this AD on U.S. operators of these
airplanes is estimated to be $2,520, or $360 per airplane.
For the other 54 airplanes, it would take approximately 12 work
hours per airplane to accomplish the proposed removal and installation,
at an average labor rate of $60 per work hour. Required parts would
cost approximately $1,200 per airplane. Based on these figures, the
total cost impact of the removal and installation proposed by this AD
on U.S. operators of these airplanes is estimated to be $103,680, or
$1,920 per airplane.
The total cost impact figured 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.
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.
[[Page 37040]]
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
Fokker: Docket 94-NM-249-AD.
-Applicability: Model F28 Mark 0100 series airplanes; as listed
in Fokker Service Bulletin SBF100-52-045, dated August 25, 1993;
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 use the authority
provided in paragraph (b) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition; or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent the opening and/or separation of the large cargo
doors while the airplane is in flight, which could result in rapid
decompression and/or structural damage to the airplane, accomplish
the following:
(a) Within 6 months after the effective date of this AD,
accomplish either paragraph (a)(1) or (a)(2) of this AD, as
applicable, in accordance with Fokker Service Bulletin SBF100-52-
045, dated August 25, 1993.
(1) For airplanes having serial numbers listed in Part 1 of the
Accomplishment Instructions of Fokker Service Bulletin SBF100-52-
045, dated August 25, 1993: Perform an inspection to determine the
torque value of the attaching parts of the interlock mechanism of
the large cargo doors, in accordance Part 1 of the Accomplishment
Instructions of the service bulletin. If the torque value is outside
the limits specified in paragraphs 2.C.(1) and 2.C.(2) of the
Accomplishment Instructions of the service bulletin, prior to
further flight, adjust the torque value in accordance with the
service bulletin.
(2) For airplanes having serial numbers listed in Part 2 of the
Accomplishment Instructions of Fokker Service Bulletin SBF100-52-
045, dated August 25, 1993: Remove the spring from the interlock
mechanism, and install a new microswitch bracket and new springs in
the interlock mechanism, in accordance with Part 2 of the
Accomplishment Instructions of the service bulletin.
(b) 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.
(c) 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 July 13, 1995.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-17707 Filed 7-18-95; 8:45 am]
BILLING CODE 4910-13-U
