[Federal Register: September 20, 2004 (Volume 69, Number 181)]
[Rules and Regulations]
[Page 56160-56161]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20se04-3]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-227-AD; Amendment 39-13796; AD 2004-19-02]
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: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to all Dassault Model Fan Jet Falcon series airplanes and
Model Mystere-Falcon 20 series airplanes, that requires 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: Effective October 25, 2004.
ADDRESSES: The service information referenced in this AD may be
obtained from Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New
Jersey 07606. This information may be examined at the Federal Aviation
Administration (FAA), Transport Airplane Directorate, Rules Docket,
1601 Lind Avenue, SW., Renton, Washington; or at the National Archives
and Records Administration (NARA). For information on the availability
of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Dassault Model Fan Jet
Falcon series airplanes and Model Mystere-Falcon 20 series airplanes
was published as a supplemental notice of proposed rulemaking (NPRM) in
the Federal Register on June 17, 2004 (69 FR 33872). That action
proposed to require inspecting and testing for fatigue cracking due to
stress corrosion in the vertical posts of the window frames in the
flight compartment. That action also proposed to add airplanes to the
applicability, to clarify which airplanes must do certain actions, and
to specify which window frames to ultrasonically inspect.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Explanation of Change Made to Final Rule
We have changed paragraphs (a)(1) and (a)(2) of this final rule to
specify that the actions shall be done in accordance with a method
approved by the Manager, International Branch, ANM-116, FAA, Transport
Airplane Directorate, or the Direction Generale de l'Aviation Civile
(or its delegated agent). In addition, 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, is listed as one
approved method for doing the detailed (endoscopic) inspection
specified in paragraph (a)(1) of this final rule. Additionally,
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, is listed as one
approved method of doing the ultrasonic test specified in paragraph
(a)(2) of this final rule.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule as proposed.
Cost Impact
The FAA estimates that 220 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 4 work hours per
airplane to accomplish the required actions, and that the average labor
rate is $65 per work hour. Based on these figures, the cost impact of
the 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 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 adopted herein will 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 final rule does not have federalism
implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a
significant economic impact, positive or negative, on a substantial
number of small entities under the criteria of the Regulatory
[[Page 56161]]
Flexibility Act. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from 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.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. Section 39.13 is amended by adding the following new airworthiness
directive:
2004-19-02 Dassault Aviation: Amendment 39-13796. Docket 2002-NM-
227-AD.
Applicability: All Model Fan Jet Falcon series airplanes and
Model Mystere-Falcon 20 series airplanes, certificated in any
category.
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
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) For airplanes that have not accomplished the actions
specified in Dassault Service Bulletin FJF-701, dated March 25,
1986; or Revision 1 dated October 22, 1987: 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 a
method approved by either the Manager, International Branch, ANM-
116, FAA, Transport Airplane Directorate; or the Direction Generale
de l'Aviation Civile (DGAC) (or its delegated agent). 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 is one approved method.
(2) For all airplanes: Do an ultrasonic test for cracking in the
posts of window frames 2, 5, 7, 8, and 10. Do the test in accordance
with a method approved by either the Manager, International Branch,
ANM-116; or the DGAC (or its delegated agent). 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 is one approved method.
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 original 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; or the DGAC (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.
Effective Date
(f) This amendment becomes effective on October 25, 2004.
Issued in Renton, Washington, on September 9, 2004.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-21051 Filed 9-17-04; 8:45 am]
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