[Federal Register Volume 60, Number 61 (Thursday, March 30, 1995)]
[Proposed Rules]
[Pages 16390-16392]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-7780]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-116-AD]


Airworthiness Directives; Fokker Model F28 Mk 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 Mk 0100 
series airplanes. This proposal would require the installation of 
modified Passenger Service Unit (PSU) panel lenses. This proposal would 
also require a one-time post-installation inspection to detect 
corrosion or deterioration of the PSU connectors, and correction of 
discrepancies, and application of sealant. This proposal is prompted by 
reports that ``No Smoking'' and ``Fasten Seat Belt'' signs installed in 
certain overhead PSU's are not readable from passengers' and flight 
attendants' seats. This proposal is also prompted by reports of smoke 
in the passenger cabin caused by overheating of the PSU connectors. The 
actions specified by the proposed AD are intended to ensure that 
warning signs are readable to passengers and flight attendants, and to 
eliminate a potential fire hazard.

DATES: Comments must be received by May 8, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 94-NM-116-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: Mark Quam, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2145; 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, [[Page 16391]] 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-116-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-116-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 Mk 0100 series 
airplanes. The RLD advises that the ``No Smoking'' and ``Fasten Seat 
Belt'' signs installed in certain overhead Passenger Service Units 
(PSU) on these airplanes may not be readable to each seated passenger 
under all probable conditions of cabin illumination. Additionally, 
these ``No Smoking'' or ``Fasten Seat Belt'' signs are not visible at 
all from the flight attendants' seats in the aft cabin. The ability to 
clearly see these signs under all conditions of illumination in the 
cabin is necessary in order to ensure that passengers and flight 
attendants are notified when smoking is not permitted on an aircraft, 
and when seat belts must be fastened. If the ``No Smoking'' signs are 
not readable or visible, passengers and flight attendants may not be 
aware of situations when smoking on the airplane could present a fire 
hazard. If the ``Fasten Seat Belts'' signs are not readable or visible, 
passengers and flight attendants may not be aware of situations when it 
is necessary that they be properly restrained in their seats to prevent 
injury during turbulent or other flight conditions.
    Additionally, the RLD advises that there have been two reports of 
smoke in the passenger aft compartment coming from a PSU. Investigation 
revealed that, in each case, the cause of the smoke was water ingress 
(condensation from the air duct) in the electrical connectors of the 
PSU. Water ingression in PSU connectors can result in corrosion of the 
contacts. Because there is a 115V (alternating) current present, the 
temperature inside the connector can rise subsequently and cause the 
connector to melt. This condition, if not corrected, can result in 
failure of the warning signs at the PSU to illuminate and could pose a 
fire hazard.
    Fokker has issued Service Bulletin SBF100-25-061, dated March 8, 
1994 (as corrected by Fokker Service Bulletin Change Notification 
SBF100-25-061/02, dated June 20, 1994), which describes procedures for 
installing modified PSU panel lenses. (This Fokker service bulletin 
refers to Grimes Aerospace Service Bulletins 10-1178-33-0036 and 10-
1178-33-0039, Revision 1, dated October 31, 1993, for additional 
installation instructions.) Certain of the modified lenses are 
configured so that the readability of the warning signs from the 
passengers' seats is improved. Other modified lenses incorporate a 
tilted legend (prisma lens) that makes readability possible from the 
aft cabin flight attendants' seats. The RLD classified this service 
bulletin as mandatory and issued Netherlands airworthiness directive 
BLA 94-078(A), dated May 11, 1994, in order to assure the continued 
airworthiness of these airplanes in the Netherlands.
    Fokker also has issued Service Bulletin SB100-25-068, dated March 
31, 1994, which describes procedures for conducting a one-time 
inspection to detect corrosion or deterioration of the PSU connectors, 
correction of discrepancies identified, and application of sealant. 
Fokker recommends that this inspection be performed after the modified 
PSU panel lenses are installed in accordance with Service Bulletin 
SBF100-25-061. The RLD has classified this service bulletin as 
``Recommended.''
    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, the proposed AD would require the installation of 
modified PSU panel lenses. This action would be required to be 
accomplished in accordance with the Fokker Service Bulletin SBF100-25-
061, described previously.
    Additionally, this proposed AD would require a one-time post-
installation inspection to detect corrosion or deterioration of the PSU 
connectors, correction of discrepancies identified, and application of 
sealant. These actions would be required to be accomplished in 
accordance with Fokker Service Bulletin SB100-25-068.
    The proposed AD would be applicable only to Model F28 Mk 0100 
series airplanes having serial numbers 11244 through 11437, inclusive. 
Beginning at serial number 11438, the modified PSU panel lenses were 
installed during production.
    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 requirement.
    The FAA estimates that 83 airplanes of U.S. registry would be 
affected by this proposed AD.
    The proposed installation of the modified PSU's would take 
approximately 2 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts would cost 
approximately $248 per airplane. Based on these figures, the total cost 
impact of the proposed installation action on U.S. operators is 
estimated to be $30,544, or $368 per airplane.
    The proposed one-time inspection of the PSU connectors would take 
approximately 5 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the total cost 
impact of the proposed inspection action on U.S. operators is estimated 
to be $24,900, or $300 per airplane.
    Based on the figures discussed above, the total cost impact of the 
proposed AD is estimated to be $55,444, or $668 per airplane. This 
total cost impact figure is [[Page 16392]] 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 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-116-AD.

    Applicability: Model F28 Mk 0100 series airplanes having serial 
numbers 11244 through 11437, inclusive; and equipped with Grimes 
Aerospace Passenger Service Units having part number (P/N) 10-1178-( 
) through P/N 10-1571-( ), inclusive; 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 (d) 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 ensure that warning signs are readable to passengers and 
flight attendants, and to eliminate a potential fire hazard, 
accomplish the following:
    (a) Within 9 months after the effective date of this AD, install 
modified Passenger Service Unit (PSU) panel lenses in accordance 
with Fokker Service Bulletin SBF100-25-061, dated March 8, 1994 (as 
corrected by Fokker Service Bulletin Change Notification SBF100-25-
061/02, dated June 20, 1994).
    (b) Prior to further flight after accomplishing the installation 
required by paragraph (a) of this AD, perform a one-time post-
installation inspection to detect corrosion and/or deterioration of 
the PSU connector, in accordance with Fokker Service Bulletin 
SBF100-25-068, dated March 31, 1994. Prior to further flight, 
correct any discrepancies detected and apply sealant in accordance 
with the service bulletin.
    (c) As of the effective date of this AD, no person shall install 
on any airplane a Grimes Aerospace Passenger Service Unit having 
part number (P/N) 10-1178-( ) through P/N 10-1571-( ), inclusive.
    (d) 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 Aircraft 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.
    (e) 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 March 24, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-7780 Filed 3-29-95; 8:45 am]
BILLING CODE 4910-13-U