[Federal Register: February 6, 2004 (Volume 69, Number 25)]
[Proposed Rules]
[Page 5767-5769]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06fe04-19]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-227-AD]
RIN 2120-AA64
Airworthiness Directives; Dassault Model Fan Jet Falcon Series
Airplanes and Model Mystere-Falcon 20 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 Dassault Model Fan Jet
Falcon series airplanes and Model Mystere-Falcon 20 series airplanes.
This proposal would require inspecting and testing for fatigue cracking
due to stress corrosion in the vertical posts of the window frames in
the flight compartment. This action is necessary to prevent fatigue
cracking of the window frames, which could result in rapid
depressurization of the fuselage and consequent reduced structural
integrity of the airplane. This action is intended to address the
identified unsafe condition.
DATES: Comments must be received by March 8, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2002-NM-227-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:
9-anm-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2002-NM-227-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 or 2000 or
ASCII text.
The service information referenced in the proposed rule may be
obtained from Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New
Jersey 07606. 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:
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.
For each issue, state what specific change to
the proposed AD is being requested.
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 2002-NM-227-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. 2002-NM-227-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the
[[Page 5768]]
airworthiness authority for France, notified the FAA that an unsafe
condition may exist on certain Model Fan Jet Falcon series airplanes
and Model Mystere-Falcon 20 series airplanes. The DGAC advises that
cracking has been found in the vertical posts of window frames in the
flight compartment that were not included in the maintenance program
inspection area. The airplane manufacturer, Dassault Aviation, has
revised certain work cards in the maintenance manual to include
procedures for inspecting and testing these window frames. Cracking of
the window frames could result in rapid depressurization of the
fuselage and consequent reduced structural integrity of the airplane.
Explanation of Relevant Service Information
Dassault has issued revised Work Card 53-30-07, ``Non-Destructive
Ultrasonic Testing of Vertical Posts on Screw-Mounted Windows'' of the
Dassault Aviation Fan Jet Falcon Maintenance Manual, dated November
2001. The work card describes procedures for testing (including
calibrating the equipment) the posts of the window frames in the flight
compartment, including the right side window, left and right rear
windows, front window, and pilot and co-pilot windows, for stress
corrosion cracking.
Dassault has also issued revised Work Card 53-30-12, ``Endoscopic
Inspection of the Frames of Pilot, Co-Pilot, and Front Glass Panels
(Aircraft Not Changed Per SB No. 701)'' of the Dassault Aviation Fan
Jet Falcon Maintenance Manual, dated November 2001. The work card
describes procedures for using an endoscope and inspecting the window
frames of the pilot, co-pilot, and front windows in the flight
compartment for stress corrosion and subsequent cracking.
Accomplishment of the actions specified in the service information is
intended to adequately address the identified unsafe condition. The
DGAC classified this service information as mandatory and issued French
airworthiness directive 2001-600-028(B), dated December 12, 2001, to
ensure the continued airworthiness of these airplanes in France.
FAA's Conclusions
These airplane models are manufactured in France 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 DGAC has kept the FAA informed
of the situation described above. The FAA has examined the findings of
the DGAC, 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 AD
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 information described previously.
This proposed AD also includes a reporting requirement.
Difference Between the Proposed AD and the French Airworthiness
Directive
The French airworthiness directive is applicable to ``all Fan Jet
Falcon and Mystere Falcon 20-(x)5 aircraft, all serial numbers.'' The
applicability of this proposed AD is ``Model Fan Jet Falcon series
airplanes and Model Mystere-Falcon 20 series airplanes; certificated in
any category; except those which have incorporated Dassault Service
Bulletin AMD-BA FJF-701, Revision 1, dated October 22, 1987.'' This
exception appears in Dassault Aviation Work Card 53-30-12, titled
``Endoscopic Inspection of the Frames of Pilot, Co-Pilot, and Front
Glass Panels (Aircraft Not Changed Per SB No. 701),'' of the Dassault
Aviation Fan Jet Falcon Maintenance Manual, dated November 2001. This
difference has been coordinated with the DGAC.
Cost Impact
The FAA estimates that 220 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 4 work
hours per airplane to accomplish the proposed actions, and that the
average labor rate is $65 per work hour. Based on these figures, the
cost impact of the proposed AD on U.S. operators is estimated to be
$57,200, or $260 per airplane.
The cost impact figure discussed above is 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 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:
Dassault Aviation: Docket 2002-NM-227-AD.
Applicability: Model Fan Jet Falcon series airplanes and Model
Mystere-Falcon 20 series airplanes; certificated in any category;
except those which have incorporated Dassault Service Bulletin AMD-
BA FJF-701, Revision 1, dated October 22, 1987.
Compliance: Required as indicated, unless accomplished
previously.
To prevent fatigue cracking of the window frames in the flight
compartment, which could result in rapid depressurization of the
[[Page 5769]]
fuselage and consequent reduced structural integrity of the
airplane, accomplish the following:
Inspection and Test of Flight Compartment Window Frames
(a) Do an inspection and test for stress corrosion and cracking
as specified in paragraphs (a)(1) and (a)(2) of this AD, at the
applicable time specified in paragraph (b) of this AD.
(1) Do a detailed inspection (using an endoscope) to detect
stress corrosion and cracking of the window frames in the flight
compartment, including the pilot, co-pilot, and front windows. Do
the inspection in accordance with Dassault Aviation Work Card 53-30-
12, titled ``Endoscopic Inspection of the Frames of Pilot, Co-Pilot,
and Front Glass Panels (Aircraft Not Changed Per SB No. 701),'' of
the Dassault Aviation Fan Jet Falcon Maintenance Manual, dated
November 2001.
(2) Do an ultrasonic test for cracking in the posts of the
window frames, including the right side window, left and right rear
windows, front window, and pilot and co-pilot windows. Do the test
in accordance with Dassault Aviation Work Card 53-30-07, titled
``Non-Destructive Ultrasonic Testing of Vertical Posts on Screw-
Mounted Windows,'' of the Dassault Aviation Fan Jet Falcon
Maintenance Manual, dated November 2001.
Note 1: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
(b) Do the inspection and test required by paragraph (a) of this
AD, at the times specified in paragraph (b)(1) or (b)(2) of this AD,
as applicable.
(1) For airplanes having 35 or more years since the date of
issuance of the original Airworthiness Certificate or the date of
issuance of the Export Certificate of Airworthiness, whichever is
first; or having accumulated 20,000 or more total flight cycles; as
of the effective date of this AD: Within 7 months after the
effective date of this AD.
(2) For airplanes not identified in paragraph (b)(1) of this AD:
Within 25 months or 2,500 flight cycles after the effective date of
this AD, whichever is first.
Repair
(c) If any stress corrosion or cracking is found during any
inspection or test required by paragraph (a) of this AD: Before
further flight, repair per a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate;
or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (or its
delegated agent).
Reporting Requirement
(d) At the applicable time specified in paragraph (d)(1) or
(d)(2) of this AD: Submit a report of the findings (positive and
negative) of the inspection required by paragraph (a) of this AD to:
Dassault Falcon Jet, Attn: Service Engineering/Falcon 20, fax: (201)
541-4706, at the applicable time specified in paragraph (d)(1) or
(d)(2) of this AD. The report must include the airplane serial
number, number of landings, number of flight hours, airplane age,
and the number and length of any cracks found. Submission of the
Charts of Records (part of French airworthiness directive 2001-600-
028(B), dated December 12, 2001), is an acceptable method of
complying with this requirement. Under the provisions of the
Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office
of Management and Budget (OMB) has approved the information
collection requirements contained in this AD and has assigned OMB
Control Number 2120-0056.
(1) If the inspection was done after the effective date of this
AD: Submit the report within 5 days after the inspection.
(2) If the inspection was done prior to the effective date of
this AD: Submit the report within 5 days after the effective date of
this AD.
Alternative Methods of Compliance
(e) In accordance with 14 CFR 39.19, the Manager, International
Branch, ANM-116, is authorized to approve alternative methods of
compliance for this AD.
Note 2: The subject of this AD is addressed in French
airworthiness directive 2001-600-028(B), dated December 12, 2001.
Issued in Renton, Washington, on January 29, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-2470 Filed 2-5-04; 8:45 am]
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