[Federal Register: March 10, 2004 (Volume 69, Number 47)]
[Rules and Regulations]
[Page 11290-11293]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr10mr04-2]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2004-NM-11-AD; Amendment 39-13508; AD 2004-05-13]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-401 and -402
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain Bombardier Model DHC-8-401 and -402 airplanes.
This action requires a records review to determine the repair/
modification status of the airplane, and follow-on and corrective
actions as necessary. This action is necessary to prevent cracks in the
lower fuselage skin due to fatigue damage in the vicinity of the Number
2 VHF antenna, which could result in rapid decompression of the
airplane. This action is intended to address the identified unsafe
condition.
DATES: Effective March 25, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 25, 2004.
Comments for inclusion in the Rules Docket must be received on or
before April 9, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2004-NM-11-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-iarcomment@faa.gov. Comments sent via the Internet must contain
``Docket No. 2004-NM-11-AD'' in the subject line and need not be
submitted in triplicate. Comments sent via fax or the Internet as
attached electronic files must be formatted in Microsoft Word 97 or
2000 or ASCII text.
The service information referenced in this AD may be obtained from
Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5, Canada.
[[Page 11291]]
This information may be examined at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA,
New York Aircraft Certification Office, 1600 Stewart Avenue, Westbury,
New York; or at the Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: David Lawson, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Westbury, New York 11590;
telephone (516) 228-7327; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION: Transport Canada Civil Aviation (TCCA),
which is the airworthiness authority for Canada, notified the FAA that
an unsafe condition may exist on certain Bombardier Model DHC-8-401 and
-402 airplanes. TCCA advises that, during an A-check on an affected
airplane, an 8-inch crack was discovered on the fuselage skin in the
vicinity of the forward Number 2 very high frequency (VHF) antenna.
Further investigation revealed cracking on four of the eight cleats
attaching the internal antenna support structure. Since the original
report, cracked cleats were found on additional airplanes. Cracking of
the fuselage skin, if not corrected, could result in rapid
decompression of the airplane.
Explanation of Relevant Service Information
Bombardier approved Repair Drawing (RD) RD8/4-53-317, Issue 2, on
December 13, 2002. The RD describes procedures for a temporary repair
of cracks in the right-hand forward center fuselage skin panel at
stringer 32S between stations X71.8 and X94.8. The repair involves
cutting away damaged skin, replacing any other damaged structure with
new parts, performing a detailed inspection for any remaining cracks,
installing an external repair doubler with filler, and reprotecting
bare areas.
Bombardier approved Modification Summary (ModSum) Package
IS4Q5300001, Revision B, on March 17, 2003. The modification involves
installing an external reinforcement doubler and replacing brackets at
the Number 2 VHF antenna installation.
Bombardier approved Repair Drawing RD8/4-53-328, Issue 1, approved
December 13, 2002, which describes procedures for replacing the support
cleats with new cleats, part number (P/N) 85307891, at stringers 32S
and 33, between stations X71.8 and X94.8.
Bombardier also approved ModSum 4-113458, Revision B-1, on
September 17, 2003, which describes procedures for reinforcing the
Number 2 VHF antenna support structure.
Bombardier issued Service Bulletin 84-53-32, Revision ``B,'' dated
November 24, 2003, which provides instructions for incorporating
Bombardier ModSum 4-113458.
Accomplishment of the applicable actions specified in the service
information is intended to adequately address the identified unsafe
condition. TCCA issued Canadian airworthiness directive CF-2003-28,
dated November 28, 2003, to ensure the continued airworthiness of these
airplanes in Canada.
FAA's Conclusions
This airplane model is manufactured in Canada and is type
certificated for operation in the United States under the provisions of
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, TCCA has kept the FAA informed of
the situation described above. The FAA has examined the findings of
TCCA, 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 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, this AD is being issued to prevent cracks in the
lower fuselage skin due to fatigue damage in the vicinity of the Number
2 antenna, which could result in rapid decompression of the airplane.
This AD requires a records review to determine repair/modification
status. For airplanes on which neither Repair Drawing RD8/4-53-317 nor
ModSum IS4Q5300001 has been incorporated, this AD requires repetitive
detailed inspections for cracking of the external surface of the
fuselage skin in the area around the Number 2 antenna and discrepancies
(cracks, deformation in the area of the bend radius, and broken rivets)
of the support cleats at stringers 32S and 33 between stations X71.8
and X94.8; replacement of all eight cleats with newly fabricated
cleats, if any cleat is discrepant; and reinforcement of cracked
fuselage skin. This AD also ultimately requires reinforcement of the
Number 2 antenna support structure (and reinforcement of the fuselage
skin around the Number 2 antenna, if not already done); the
reinforcement actions terminate the repetitive inspections.
Difference Between FAA and TCCA Airworthiness Directives
The Canadian airworthiness directive refers to ``detailed visual
inspections'' for various discrepancies. We have determined that these
procedures constitute ``detailed inspections.'' Note 1 in this AD
defines this type of inspection.
Determination of Rule's Effective Date
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
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 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 rule that might
suggest a need to modify the 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 that
summarizes each FAA-public contact
[[Page 11292]]
concerned with the substance of this AD will be filed in the Rules
Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2004-NM-11-AD.'' The postcard will be date stamped and
returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, 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, Incorporation by
reference, 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:
2004-05-13 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-13508. Docket 2004-NM-11-AD.
Applicability: Model DHC-8-401 and -402 airplanes, certificated
in any category, serial numbers 4003 through 4076 inclusive, and
4078 through 4081 inclusive.
Compliance: Required as indicated, unless accomplished
previously.
To prevent cracks in the lower fuselage skin due to fatigue
damage in the vicinity of the Number 2 VHF antenna, which could
result in rapid decompression of the airplane, accomplish the
following:
Records Review
(a) Within the applicable compliance time specified in Table 1
of this AD, review the airplane maintenance records to determine if
the airplane has been modified or repaired in accordance with
Bombardier Repair Drawing RD8/4-53-317, Issue 2, approved December
13, 2002, or earlier issue; or Bombardier Modification Summary
(ModSum) Package IS4Q5300001, Revision B, approved March 17, 2003,
or earlier issue.
Table 1.--Compliance Time for Records Review
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If the total flight hours accumulated on the airplane,
as of the effective date of this AD, is-- Then review the records--
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<=1,450................................................ Before the accumulation of 1,900 total flight hours.
1,450 and <=2,200........................... Within 300 flight hours after the effective date of
this AD.
2,200 and <=3,000........................... Within 150 flight hours after the effective date of
this AD.
3,000....................................... Within 50 flight hours after the effective date of this
AD.
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Follow-on Actions: Drawing/ModSum Incorporated
(b) If either Bombardier Repair Drawing RD8/4-53-317 or
Bombardier ModSum IS4Q5300001, as specified in paragraph (a) of this
AD, has been incorporated before the effective date of this AD: Do
the terminating action required by, and at the time specified in,
paragraph (d) of this AD.
Follow-on Actions: Drawing/ModSum Not Incorporated
(c) If neither Bombardier Repair Drawing RD8/4-53-317 nor
Bombardier ModSum IS4Q5300001, as specified in paragraph (a) of this
AD, has been incorporated before the effective date of this AD:
Before further flight, do the actions specified in paragraphs (c)(1)
and (c)(2) of this AD.
(1) Perform a detailed inspection for cracking of the external
surface of the fuselage skin in the area around the Number 2 VHF
antenna, in accordance with Bombardier Service Bulletin 84-53-32,
Revision B, dated November 24, 2003. Use a 10X magnifying glass and
appropriate lighting to do the inspection.
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.''
(i) If any crack is found: Before further flight, do the actions
specified in paragraphs (c)(1)(i)(A) and (c)(1)(i)(B) of this AD.
(A) Repair in accordance with Bombardier Repair Drawing RD8/4-
53-317, Issue 2, approved December 13, 2002.
(B) Replace all 8 support cleats, part number (P/N) 85307891, at
stringers 32S and 33, between stations X71.8 and X94.8, in
accordance with Repair Drawing RD8/4-53-328, Issue 1, approved
December 13, 2002.
(ii) If no crack is found: Before further flight, do the
requirements of paragraph (c)(2) of this AD.
(2) Do a detailed inspection to detect discrepancies (cracks,
deformation in the area of the bend radius, and broken rivets) of
the support cleats, P/N 85307891, at stringers 32S and 33, between
stations X71.8 and X94.8; in accordance with Bombardier Service
Bulletin 84-53-32, Revision B, dated November 24, 2003.
(i) If any discrepancy is found: Before further flight, remove
the antenna and do a detailed inspection for cracks of the external
surface of the fuselage skin underneath the antenna, in accordance
with Bombardier Service Bulletin 84-53-32, Revision B, dated
November 24, 2003. Use a 10X magnifying glass and appropriate
lighting to do the inspection.
(A) If no crack is found: Before further flight, reinforce the
fuselage skin around the Number 2 VHF antenna and replace all 8
support cleats with new cleats, P/N 85307891, at stringers 32S and
33, between stations X71.8 and X94.8. Do the actions in accordance
with Bombardier ModSum IS4Q5300001, Revision B, approved March 17,
2003.
(B) If any crack is found: Before further flight, repair in
accordance with Bombardier Repair Drawing RD8/4-53-317, Issue 2,
approved December 13, 2002; and replace all 8 support cleats with
new cleats, P/N 85307891, at stringers 32S and 33, between stations
X71.8 and X94.8, in accordance with Bombardier Repair Drawing RD8/4-
53-328, Issue 1, approved December 13, 2002.
[[Page 11293]]
(ii) If no discrepancy is found: Repeat the inspections required
by paragraph (c)(1) of this AD at the following times, as
applicable:
(A) If all 8 cleats have not been replaced: Repeat the
inspections at intervals not to exceed 200 flight hours until
accomplishment of the terminating action required by paragraph (d)
of this AD.
(B) If all 8 cleats have been replaced: Repeat the inspections
at intervals not to exceed 500 flight hours until accomplishment of
the terminating action required by paragraph (d) of this AD.
Terminating Action
(d) Within 4,000 flight hours after the effective date of this
AD, do the actions specified in paragraphs (d)(1) and (d)(2), as
applicable, of this AD. Accomplishment of the applicable
requirements of this paragraph terminates the repetitive inspections
required by paragraph (c) of this AD.
(1) For all airplanes: Reinforce the Number 2 VHF antenna
support structure in accordance with Bombardier ModSum 4-113458,
Revision B-1, approved September 17, 2003. Bombardier Service
Bulletin 84-53-32, Revision B, dated November 24, 2003, provides
instructions for incorporating ModSum 4-113458.
(2) For airplanes on which neither Bombardier Repair Drawing
RD8/4-53-317 nor Bombardier ModSum IS4Q5300001 has been
incorporated: Reinforce the fuselage skin around the Number 2 VHF
antenna in accordance with Bombardier ModSum IS4Q5300001, Revision
B, approved March 17, 2003.
Alternative Methods of Compliance
(e) In accordance with 14 CFR 39.19, the Manager, New York
Aircraft Certification Office (ACO), FAA, is authorized to approve
alternative methods of compliance for this AD.
Incorporation by Reference
(f) Unless otherwise specified in this AD, the actions must be
done in accordance with the Bombardier modification summary packages
and repair drawings listed in Table 2 of this AD, as applicable.
(The approval date of the repair drawings and modification summary
packages appears only on the first page of these documents.)
Table 2.--Applicable Service Documents
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Revision level shown
Document Page number on the page Date shown on the page
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Bombardier Modification Summary 1-3, 6............... Revision B.......... March 17, 2003.
Package IS4Q5300001.
4, 5................. Revision A.......... December 22, 2002.
Bombardier Repair Drawing RD8/4-53- 1, 2................. Issue 2............. December 13, 2002.
317.
3-5.................. Issue 1............. December 11, 2002.
Bombardier Repair Drawing RD8/4-53- All.................. Issue 1............. December 13, 2002.
328.
Bombardier Modification Summary All.................. Revision B-1........ September 17, 2003.
Package 4-113458.
Bombardier Service Bulletin 84-53- All.................. Revision `B'........ November 24, 2003.
32.
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This incorporation by reference was approved by the Director of
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Copies may be obtained from Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt Boulevard, Downsview,
Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the FAA, New York Aircraft Certification Office,
1600 Stewart Avenue, Westbury, New York; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
Note 2: The subject of this AD is addressed in Canadian
airworthiness directive CF-2003-28, dated November 28, 2003.
Effective Date
(g) This amendment becomes effective on March 25, 2004.
Issued in Renton, Washington, on February 25, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-4682 Filed 3-9-04; 8:45 am]
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