[Federal Register Volume 63, Number 225 (Monday, November 23, 1998)]
[Rules and Regulations]
[Pages 64609-64612]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-31178]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-299-AD; Amendment 39-10903; AD 98-24-18]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-100 and -300
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain Bombardier Model DHC-8-102 and -103 series
airplanes, that currently requires a one-time inspection to detect
disbonding of the upper and lower skin panels of the horizontal
stabilizer, and repair, if necessary. This amendment establishes
repetitive intervals for the inspection to detect disbonding of the
upper and lower skin panels of the horizontal stabilizer. This
amendment also revises the applicability of the existing AD to include
certain additional airplanes, and to exclude certain other airplanes.
This amendment is prompted by issuance of mandatory continuing
airworthiness information by a foreign civil airworthiness authority.
The actions specified by this AD are intended to prevent reduced
strength capability and consequent failure of the horizontal
stabilizer, which could result in loss of controllability of the
airplane.
DATES: Effective December 8, 1998.
Comments for inclusion in the Rules Docket must be received on or
before December 23, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-299-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
[[Page 64610]]
The service information referenced in this AD may be obtained from
Bombardier, Inc., Bombardier Regional Aircraft Division, Garratt
Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be
examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue,
SW., Renton, Washington; or at the FAA, Engine and Propeller
Directorate, New York Aircraft Certification Office, 10 Fifth Street,
Third Floor, Valley Stream, New York.
FOR FURTHER INFORMATION CONTACT: Serge Napoleon, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, Engine and Propeller
Directorate, New York Aircraft Certification Office, 10 Fifth Street,
Third Floor, Valley Stream, New York 11581; telephone (516) 256-7512;
fax (516) 568-2716.
SUPPLEMENTARY INFORMATION: On March 5, 1998, the FAA issued AD 98-05-
03, amendment 39-10389 (63 FR 11987, March 12, 1998), applicable to
certain Bombardier (formerly de Havilland) Model DHC-8-102 and -103
series airplanes, to require a one-time inspection to detect disbonding
of the upper and lower skin panels of the horizontal stabilizer, and
repair, if necessary. That action was prompted by issuance of mandatory
continuing airworthiness information by a foreign civil airworthiness
authority. The actions required by that AD are intended to prevent
reduced strength capability and consequent failure of the horizontal
stabilizer, which can result in loss of controllability of the
airplane.
Actions Since Issuance of Previous Rule
Transport Canada Aviation (TCA), which is the airworthiness
authority for Canada, notified the FAA that, during the one-time
inspection performed in accordance with AD 98-05-03 and the parallel
Canadian airworthiness directive CF-98-01, disbonding of doublers and
stringers from the upper and lower skin of the horizontal stabilizer
was detected on several Model DHC-8-102 and -103 series airplanes.
Because these airplanes were close together in serial number, the
problem of disbonding was attributed to discrepancies in the bonding
process on a single batch of skin panels installed on certain
Bombardier Model DHC-8-102 and -103 series airplanes.
As a result of these findings, TCA issued Canadian airworthiness
directive CF-98-24, dated August 19, 1998, to require repetitive
ultrasonic inspections to detect disbonding of the upper and lower skin
panels of the horizontal stabilizer. During repeat inspections
performed in accordance with that airworthiness directive, disbonding
was detected on several airplanes on which no disbonding was detected
during the initial inspection.
Based on the information provided by TCA, the FAA has determined
that the one-time inspection required by AD 98-05-03 may not be
adequate to detect disbonding of the upper and lower skin panels of the
horizontal stabilizer and, therefore, may not be providing an adequate
level of safety for the transport airplane fleet.
FAA's Conclusions
This airplane model is manufactured in Canada 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, TCA has kept the FAA informed of the
situation described above. The FAA has examined the findings of TCA,
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 supersedes AD 98-05-03 to require
repetitive ultrasonic inspections to detect disbonding of the upper and
lower skin panels of the horizontal stabilizer, and repair, if
necessary. In addition, this AD also revises the applicability of the
existing AD to include certain additional airplanes, and to exclude
certain other airplanes. This AD also requires that operators report
inspection results, both positive and negative findings, to Bombardier.
Interim Action
This is considered to be interim action until final action is
identified, at which time the FAA may consider further rulemaking.
Differences Between This Rule and the Foreign Airworthiness
Directive
Operators should note that the parallel Canadian airworthiness
directive CF-98-24 specifies that any disbonding that is detected that
is beyond the local disbonding limits specified in de Havilland Product
Support Manual (PSM) 1-8-7A, part 5, section 55-00-01, dated July 15,
1996, shall be repaired prior to further flight. However, this AD
requires that all disbonding, whether it is within or beyond the
limits, be repaired prior to further flight. This AD also specifies
that disbonding that exceeds the limits specified in the PSM must be
repaired in accordance with a method approved by the FAA.
Explanation of Applicability
Operators should note that AD 98-05-03 and parallel Canadian
airworthiness directive CF-98-01, dated February 19, 1998, are
applicable to Model DHC-8-102 and -103 series airplanes having serial
numbers 003 through 050 inclusive. Since the issuance of AD 98-05-03,
TCA has advised the FAA that the serial numbers of the airplanes may
differ from the Canadian Aviation Products (CAP) serial number of the
horizontal stabilizer. Therefore, it may be necessary for operators to
check the data plate located on the left side of the horizontal
stabilizer to determine the serial number of the horizontal stabilizer.
Also, the applicability of Canadian airworthiness directive CF-98-24
includes additional airplanes. For these reasons, this AD (and parallel
Canadian airworthiness directive CF-98-24) is applicable to Model DHC-
8-100 and -300 series airplanes equipped with a CAP horizontal
stabilizer having serial numbers CAP 003 through CAP 214 inclusive.
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
[[Page 64611]]
additional rulemaking action would be needed.
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 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 98-NM-299-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
The regulations adopted herein will 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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, Safety.
Adoption of the Amendment
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
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 removing amendment 39-10389 (63 FR
11987, March 12, 1998), and by adding a new airworthiness directive
(AD), amendment 39-10903, to read as follows:
98-24-18 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-10903. Docket 98-NM-299-AD. Supersedes AD 98-05-03, Amendment 39-
10389.
Applicability: Model DHC-8-100 and -300 series airplanes,
equipped with Canadian Aviation Products (CAP) horizontal
stabilizers having Serial Numbers CAP 003 through CAP 214 inclusive,
certificated in any category.
Note 1: It may be necessary to check the data plate on the left
side of the horizontal stabilizer to determine the serial number of
the horizontal stabilizer, because the serial number of the
horizontal stabilizer may not be the same as the airplane serial
number.
Note 2: 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 (f)(1)
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 prevent reduced strength capability and consequent failure of
the horizontal stabilizer, which could result in loss of
controllability of the airplane, accomplish the following:
Restatement of Requirements of AD 98-05-03
Note 3: Accomplishment of the actions required by paragraph (a)
of this AD is not intended to supersede the ongoing requirements of
the Airworthiness Limitation identified in the Maintenance Review
Board (MRB) report as Task 5500/01.
(a) For Model DHC-8-102 and -103 series airplanes having Serial
Numbers 003 through 050 inclusive: Perform a one-time ultrasonic
bond inspection to detect disbonding of the upper and lower skin
panels of the horizontal stabilizer, at the time specified in
paragraph (a)(1) or (a)(2) of this AD, as applicable; in accordance
with de Havilland Product Support Manual (PSM) 1-8-7A, part 5,
section 55-00-01, dated July 15, 1996.
(1) For airplanes having Serial Numbers 010 through 040
inclusive: Inspect within 20 flight cycles or 7 days after March 17,
1998 (the effective date of AD 98-05-03, amendment 39-10389),
whichever occurs first.
(2) For airplanes having Serial Numbers 003 through 009
inclusive and 041 through 050 inclusive: Inspect within 60 flight
cycles or 7 days after March 17, 1998, whichever occurs first.
(b) If any disbonding is found during the inspection required by
paragraph (a) of this AD: Prior to further flight, accomplish the
actions specified by paragraph (b)(1), (b)(2), or (b)(3) of this AD,
as applicable.
(1) If the disbonding is below (smaller than) the limits
specified in the PSM, no further action is required by this
paragraph.
(2) If the disbonding is within the limits specified in the PSM,
repair the disbonded area in accordance with the DHC-8 Structural
Repair Manual PSM 1-8-3.
(3) If the disbonding exceeds the limits specified in the PSM or
if a repair is not provided by the PSM, repair the disbonded area in
accordance with a method approved by the Manager, New York Aircraft
Certification Office (ACO), FAA, Engine and Propeller Directorate.
Note 4: Where differences between this AD and the parallel
Canadian airworthiness directive exist, this AD prevails.
(c) Within 2 days after performing the inspection required by
paragraph (a) of this AD: Submit a report of inspection findings,
regardless of the results, to the Manager, New York ACO, FAA, Engine
and Propeller Directorate, 10 Fifth Street, Third Floor, Valley
Stream, New York 11581; fax (516) 568-2716. The report must include
the airplane serial number, the stringer number, and the extent
(length or surface area) of disbonding. For inspections performed
after the effective date of this AD, reports also must include the
horizontal stabilizer CAP number. (Operators may follow the
guidelines provided in Figure 2 of de Havilland PSM 1-8-7A for
reporting requirements.) Information collection requirements
contained in this regulation have been approved by the Office of
Management and Budget (OMB) under the provisions of the Paperwork
Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been
assigned OMB Control Number 2120-0056.
New Requirements of This AD
(d) For Model DHC-8-100 and -300 series airplanes equipped with
CAP horizontal stabilizers having serial numbers CAP 003 through CAP
214 inclusive: Perform an ultrasonic bond inspection to detect
disbonding of the upper and lower skin panels of the horizontal
stabilizer, in accordance with de Havilland Product Support Manual
(PSM) 1-8-7A, part 5, section 55-00-01, dated July 15, 1996; at the
time specified in paragraph (d)(1) or (d)(2) of this AD, as
applicable.
(1) For Model DHC-8-100 and -300 series airplanes equipped with
CAP horizontal stabilizers having serial numbers CAP 003 through CAP
050 inclusive: Inspect within 1 month after the effective date of
this AD, unless accomplished within 1 month prior to the effective
date of this AD.
[[Page 64612]]
(i) If no disbonding is detected, repeat the inspection one time
within 14 months after the most recent inspection, but no earlier
than 12 months after the most recent inspection. Thereafter, repeat
the inspection at intervals not to exceed 2 years after the most
recent inspection.
(ii) If any disbonding is detected, prior to further flight,
accomplish the actions specified by paragraph (b)(1), (b)(2), or
(b)(3) of this AD, as applicable. Repair of the disbonded area in
accordance with the DHC-8 Structural Repair Manual PSM 1-8-3
constitutes terminating action for the repetitive inspection
requirements specified in paragraph (d)(1)(i) of this AD.
(2) For Model DHC-8-100 and -300 series airplanes equipped with
CAP horizontal stabilizers having serial numbers CAP 051 through CAP
214 inclusive: Inspect at the next regularly scheduled maintenance
period, but no later than 90 days after the effective date of this
AD, unless the inspection was accomplished within 10 months prior to
the effective date of this AD.
(i) If no disbonding is detected, repeat the inspection
thereafter at intervals not to exceed 2 years. For airplanes that
were inspected within 10 months prior to the effective date of this
AD, repeat the inspection at an interval not to exceed 2 years after
the most recent inspection, and thereafter at intervals not to
exceed 2 years.
(ii) If any disbonding is detected, prior to further flight,
accomplish the actions specified by paragraph (b)(1), (b)(2), or
(b)(3) of this AD, as applicable. Repair of the disbonded area in
accordance with the DHC-8 Structural Repair Manual PSM 1-8-3
constitutes terminating action for the repetitive inspection
requirements specified in paragraphs (d)(2)(i) of this AD for the
repaired area.
(e) For any inspection performed in accordance with paragraph
(d) of this AD, submit a report of inspection findings, regardless
of the results, to Bombardier Aerospace Regional Aircraft Technical
Services, phone (416) 375-4000, fax (416) 375-4539. Submit the
report at the time specified in paragraph (e)(1), (e)(2), or (e)(3)
of this AD, as applicable. The report must include the airplane
serial number, horizontal stabilizer CAP number, and the extent
(length or surface area) of disbonding. (Operators may follow the
guidelines provided in Figure 2 of de Havilland PSM 1-8-7A for
reporting requirements.) Information collection requirements
contained in this regulation have been approved by the OMB under the
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et
seq.) and have been assigned OMB Control Number 2120-0056.
(1) For any inspection performed after the effective date of
this AD: Submit a report within 7 days after the inspection.
(2) For inspections performed within 1 month prior to the
effective date of this AD, as specified in paragraph (d)(1) of this
AD: Submit a report within 7 days after the effective date of this
AD.
(3) For inspections performed within 10 months prior to the
effective date of this AD, as specified in paragraph (d)(2) of this
AD: Submit a report within 7 days after the effective date of this
AD.
(f)(1) 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, New York ACO. Operators shall
submit their requests through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, New York ACO.
(f)(2) Alternative methods of compliance, approved previously in
accordance with AD 98-05-03, amendment 39-10389, are approved as
alternative methods of compliance with this AD.
Note 5: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the New York ACO.
(g) 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 6: The subject of this AD is addressed in Canadian
airworthiness directive CF-98-24, dated August 19, 1998.
(h) This amendment becomes effective on December 8, 1998.
Issued in Renton, Washington, on November 16, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-31178 Filed 11-20-98; 8:45 am]
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