[Federal Register Volume 61, Number 13 (Friday, January 19, 1996)]
[Proposed Rules]
[Pages 1294-1295]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-492]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-164-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. This proposal would require installation of 
reinforcement plates under each hook latch fitting on the frame of each 
large cargo door. For some airplanes, this proposal would require 
inspection to detect cracking in the area around each hook latch 
fitting, and repair, if necessary. This proposal is prompted by the 
results of stress analyses and destructive tests which revealed that 
fatigue-related cracking may develop in the vicinity of the hook latch 
fittings on the frame of the large cargo doors. The actions specified 
by the proposed AD are intended to prevent reduced structural integrity 
of the frames of the cargo door due to fatigue cracking, which may lead 
to the cargo door(s) opening while the airplane is in flight.

DATES: Comments must be received by February 21, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-164-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: Ruth Harder, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-1721; fax (206) 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 95-NM-164-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. 95-NM-164-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 the results of stress analyses and 
destructive tests on the frames of Model F28 Mark 0100 large cargo 
doors have shown that fatigue-related cracking may develop in the area 
of the hook latch fittings. Test data have shown that such cracking is 
most likely to develop after 11,000 flight cycles. This condition, if 
not detected and corrected in a timely manner, could result in reduced 
structural integrity of the frames of the large cargo door, which may 
lead to the cargo door(s) opening while the airplane is in flight.
    Fokker has issued Service Bulletin SBF100-52-050, Revision 1, dated 
September 14, 1994, which describes procedures for installing 
reinforcement plates under each hook latch fitting on the frame of each 
large cargo door. The RLD classified this service bulletin as mandatory 
and issued Dutch airworthiness directive BLA 94-157 (A), dated November 
24, 1994, 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, the 
proposed AD would require installation of two reinforcement plates 
under each hook latch fitting on the frame of each large cargo door. 
The installation would be required to be accomplished in accordance 
with the service bulletin described previously.
    This AD also proposes to require, for certain airplanes, an 
inspection to detect cracking in the area around each hook latch 
fitting on the frame of each large cargo door and repair of any 
cracking found, in accordance with a method approved by the FAA.
    The FAA estimates that 100 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 4.5 work 
hours per airplane to accomplish the proposed installation, and that 
the average labor rate is $60 per work hour. Required parts would cost 
approximately $10,000 per airplane. Based on these figures, the cost 
impact of the proposed installation on U.S. operators is estimated to 
be $1,027,000, or $10,270 per airplane.
    The FAA estimates that it would take approximately 4.5 work hours 
per airplane to accomplish the proposed inspection (that is required 
for certain airplanes), and that the average labor

[[Page 1295]]

rate is $60 per work hour. Based on these figures, the cost impact of 
the proposed inspection is estimated to be $270 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.
    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 USC 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

Fokker: Docket 95-NM-164-AD.

    Applicability: Model F28 Mark 0100 series airplanes, as listed 
in Fokker Service Bulletin SBF100-52-050, Revision 1, dated 
September 14, 1994, 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 use the authority 
provided in paragraph (c) 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 reduced structural integrity of the frame of the 
large cargo door, which may lead to the cargo door(s) opening while 
the airplane is in flight, accomplish the following:
    (a) Prior to the accumulation of 11,000 total flight cycles or 
within 500 flight cycles after the effective date of this AD, 
whichever occurs later, install two reinforcement plates under each 
hook latch fitting on the frame of each large cargo door, in 
accordance with the Accomplishment Instructions of Fokker Service 
Bulletin SBF100-52-050, Revision 1, dated September 14, 1994.
    (b) For airplanes that have accumulated 11,000 or more total 
flight cycles at the time of compliance with paragraph (a) of this 
AD: Concurrent with the accomplishment of the requirements of 
paragraph (a) of this AD, perform an inspection to detect cracking 
in the area around each hook latch fitting on the frame of each 
large cargo door, in accordance with a method approved by the 
Manager, Standardization Branch, ANM-113, FAA, Transport Airplane 
Directorate.
    (1) If no cracking is detected, no further action is required by 
this paragraph.
    (2) If any cracking is detected, prior to completing the 
requirements of paragraph (a) of this AD, repair in accordance with 
a method approved by the Manager, Standardization Branch, ANM-113.
    (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. 
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 January 10, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-492 Filed 1-18-96; 8:45 am]
BILLING CODE 4910-13-U