[Federal Register Volume 67, Number 225 (Thursday, November 21, 2002)]
[Proposed Rules]
[Pages 70189-70191]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-29678]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-334-AD]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F.28 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

[[Page 70190]]

Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes. 
This proposal would require repetitive inspections for discrepancies of 
the internal fuselage skin panels located in the stub wing areas; and 
corrective action if necessary. This action is necessary to detect and 
correct heat damage to the fuselage skin panels caused by the leakage 
of hot air from one of the bleed air ducts inside the stub wing, which 
could result in reduced structural integrity of the engine support 
structure. This action is intended to address the identified unsafe 
condition.

DATES: Comments must be received by December 23, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-334-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-334-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, 
the Netherlands. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1137; 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 action may be changed in 
light of the comments received.
    Submit comments using the following format:
    [sbull] Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    [sbull] For each issue, state what specific change to the proposed 
AD is being requested.
    [sbull] Include justification (e.g., reasons or data) for each 
request.
    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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-334-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-114, Attention: Rules 
Docket No. 2001-NM-334-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Civil Aviation Authority--The Netherlands (CAA-NL), which is 
the airworthiness authority for the Netherlands, notified the FAA that 
an unsafe condition may exist on all Fokker Model F.28 Mark 1000, 2000, 
3000, and 4000 series airplanes. The CAA-NL advises that it has 
received reports of heat damage to the internal fuselage skin panels 
located in the stub wing areas. The cause of the heat damage was the 
leakage of hot air from one of the bleed air ducts inside the stub 
wing. Evidence of the heat damage was yellow discoloration of the 
primer paint on the inside of the fuselage. This condition, if not 
corrected, could result in reduced structural integrity of the engine 
support structure.

Explanation of Relevant Service Information

    Fokker Services B.V. has issued Service Bulletin F28/53-151, dated 
June 4, 2001. The service bulletin describes procedures for repetitive 
visual inspections of the internal fuselage skin panels in the stub 
wing areas to detect discoloration of the primer paint due to heat 
damage, buckling or waviness of the skin panel, loose or missing 
fasteners, or fasteners with sheared-off heads; and corrective actions 
if necessary. The corrective actions include an eddy current 
inspection; measurement of the length and depth of buckles or waves in 
the skin panel; repair or replacement of skin panels with heat damage, 
buckling, or waviness that are not within the acceptable limits 
specified in the service bulletin; and replacement of loose and/or 
missing fasteners, or fasteners having sheared-off heads, with new 
fasteners. The CAA-NL classified this service bulletin as mandatory and 
issued Dutch airworthiness directive 2001-093, dated July 31, 2001, in 
order to assure the continued airworthiness of these airplanes in the 
Netherlands.

FAA's Conclusions

    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 CAA-NL has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the CAA-NL, 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 bulletin described previously.

Interim Action

    This is considered to be an interim action until a final action is 
identified, at which time the FAA may consider further rulemaking.

[[Page 70191]]

Cost Impact

    The FAA estimates that 24 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 AD on U.S. operators is estimated to be 
$1,440, or $60 per airplane, per inspection cycle.
    The cost impact figure discussed above is based on the assumption 
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 proposed AD were not adopted. The cost impact 
figures discussed in AD rulemaking actions represent only the time 
necessary to perform the specific actions actually required by the AD. 
These figures typically do not include incidental costs, such as the 
time required to gain access and close up, planning time, or time 
necessitated by other administrative actions.

Regulatory Impact

    The regulations proposed herein would not have a substantial direct 
effect 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, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    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 Services B.V.: Docket 2001-NM-334-AD.

    Applicability: All Model F.28 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 
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 (e) 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 detect and correct heat damage to the fuselage skin panels 
caused by the leakage of hot air from one of the bleed air ducts 
inside the stub wing, and consequent reduced structural integrity of 
the engine support structure; accomplish the following:

Repetitive Inspections

    (a) Within 6,000 flight cycles after the effective date of this 
AD: Perform a general visual inspection of the internal fuselage 
structure between frames 16060 and 16660 and the beams at the upper 
and lower stub wing angles in the stub wing (engine pylon) areas, 
for discoloration of the primer paint, buckling or waviness of the 
skin panel, loose and/or missing fasteners, or fasteners with 
sheared-off heads, by accomplishing all actions specified in Part 1 
of the Accomplishment Instructions of Fokker Service Bulletin F28/
53-151, dated June 4, 2001. Repeat the inspection at intervals not 
to exceed 6,000 flight cycles.

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made from within 
touching distance unless otherwise specified. A mirror may be 
necessary to enhance visual access to all exposed surfaces in the 
inspection area. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or droplight and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

Corrective Actions

    (b) Except as provided by paragraph (c) of this AD, if any 
discrepancy is found (i.e., primer paint discoloration; buckling or 
waviness of the skin panel; missing, damaged, or loose rivets) 
during the general visual inspection required by paragraph (a) of 
this AD, before further flight, perform the applicable follow-on 
corrective actions (e.g., eddy current inspection; measurement of 
the length and depth of buckles or waves in the skin panel; repair 
of skin panels with heat damage, buckling, or waviness that are not 
within the acceptable limits specified in the service bulletin, or 
replacement with new skin panels; and replacement of loose and/or 
missing fasteners, or fasteners having sheared-off heads with new 
fasteners; as applicable) specified in the Accomplishment 
Instructions of Fokker Service Bulletin F28/53-151, dated June 4, 
2001.
    (c) If buckling or waviness of the skin panel is detected during 
the general visual inspection required by paragraph (a) of this AD, 
and the depth is within the limits specified in Part 2, paragraph 
C.(2) of the Accomplishment Instructions of Fokker Service Bulletin 
F28/53-151, dated June 4, 2001, the affected area must be repaired 
within 2,000 flight cycles after accomplishment of the inspection 
required by paragraph (a) of this AD.
    (d) Repair or replacement of damaged fuselage skin panels or 
fasteners does not terminate the repetitive inspections required by 
this AD.

Alternative Methods of Compliance

    (e) 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, 
Transport Airplane Directorate, FAA. 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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (f) 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 4: The subject of this AD is addressed in Dutch 
airworthiness directive 2001-093, dated July 31, 2001.


    Issued in Renton, Washington, on November 15, 2002.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-29678 Filed 11-20-02; 8:45 am]
BILLING CODE 4910-13-P