[Federal Register Volume 67, Number 123 (Wednesday, June 26, 2002)]
[Rules and Regulations]
[Pages 42989-42992]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-15367]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-69-AD; Amendment 39-12783; AD 2002-12-11]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-100, -200, and -
300 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 certain Bombardier Model DHC-8-100, -200, and -300 series 
airplanes, that requires revision of the applicable maintenance program 
manual, repetitive inspections for corrosion or cracking of the hook 
roller shafts of the flap carriage, and eventual replacement of the 
hook roller shafts with new or serviceable hook roller shafts. This 
replacement extends the interval for the repetitive inspections. This 
action is necessary to prevent cracking of the hook roller shafts of 
the flap carriage and consequent reduced structural integrity of the 
flap, which could result in jamming of the flap. This

[[Page 42990]]

action is intended to address the identified unsafe condition.

DATES: Effective July 31, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 31, 2002.

ADDRESSES: 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. 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 FAA, New York Aircraft Certification 
Office, 10 Fifth Street, Third Floor, Valley Stream, New York; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dan Parrillo, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-172, FAA, New York Aircraft 
Certification Office, 10 Fifth Street, Third Floor, Valley Stream, New 
York 11581; telephone (516) 256-7505; fax (516) 568-2716.

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 Bombardier Model DHC-8-
100, -200, and -300 series airplanes was published in the Federal 
Register on March 21, 2002 (67 FR 13108). That action proposed to 
require revision of the applicable maintenance program manual; 
repetitive inspections for corrosion or cracking of the hook roller 
shafts of the flap carriage; and eventual replacement of the hook 
roller shafts with new or serviceable hook roller shafts, which would 
extend the interval for the repetitive inspections.

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 to Final Rule

    The FAA has revised paragraph (a) of the final rule to clarify that 
the maintenance manual revision must be accomplished according to the 
applicable temporary revision listed in paragraph (a)(1), (a)(2), or 
(a)(3) of the AD.

Conclusion

    After careful review of the available data, the FAA has determined 
that air safety and the public interest require the adoption of the 
rule with the change described previously. The FAA has determined that 
this change will neither increase the economic burden on any operator 
nor increase the scope of the AD.

Cost Impact

    The FAA estimates that 183 airplanes of U.S. registry will be 
affected by this AD.
    It will take approximately 4 work hours per airplane to accomplish 
the required inspection, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the required inspection on 
U.S. operators is estimated to be $43,920, or $240 per airplane, per 
inspection cycle.
    It will take approximately 4 work hours per airplane to accomplish 
the required replacement, at an average labor rate of $60 per work 
hour. Required parts will cost approximately $460 per airplane. Based 
on these figures, the cost impact of the required replacement on U.S. 
operators is estimated to be $128,100, or $700 per airplane.
    The cost impact figures discussed above are 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 
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, Incorporation by 
reference, 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 adding the following new 
airworthiness directive:

2002-12-11  Bombardier, Inc. (Formerly de Havilland, Inc.): 
Amendment 39-12783. Docket 2001-NM-69-AD.

    Applicability: Model DHC-8-100, -200, and -300 series airplanes; 
serial numbers 3 through 555 inclusive; 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 prevent cracking of the hook roller shafts of the flap 
carriage and consequent reduced structural integrity of the flap, 
which could result in jamming of the flap, accomplish the following:

Revision of Maintenance Program Manual

    (a) Within 30 days after the effective date of this AD, 
accomplish paragraph (a)(1), (a)(2), or (a)(3) of this AD according 
to the service information specified, as applicable.

[[Page 42991]]

    (1) For Model DHC-8-100 series airplanes: Insert de Havilland 
Inc. Dash 8 Airworthiness Limitations List Temporary Revisions (TRs) 
AWL-75 and AWL-76, both dated July 14, 2000, into de Havilland Inc. 
Dash 8 Series 100 Maintenance Program Manual PSM 1-8-7.
    (2) For Model DHC-8-200 series airplanes: Insert de Havilland 
Inc. Airworthiness Limitations List TR AWL 2-19, dated July 14, 
2000, into de Havilland Inc. Dash 8 Series 200 Maintenance Program 
Manual PSM 1-82-7.
    (3) For Model DHC-8-300 series airplanes: Insert de Havilland 
Inc. Airworthiness Limitations List TR AWL 3-83, dated July 14, 
2000, into de Havilland Inc. Dash 8 Series 300 Maintenance Program 
Manual PSM 1-83-7.

Repetitive Inspections

    (b) Do a detailed inspection for corrosion or cracking of the 
hook roller shafts of the flap carriage, at the times specified in 
paragraph (b)(1), (b)(2), or (b)(3) of this AD, as applicable; and 
according to the service information in paragraph (b)(1), (b)(2), or 
(b)(3) of this AD, as applicable.

    Note 2: 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.''

    (1) For Model DHC-8-100 series airplanes: For Pre Mod 8Q101103 
roller shafts having part number (P/N) 85750362-103 or 85750362-105, 
do the initial inspection at the compliance time specified in the 
``Threshold'' column of the table in de Havilland Inc. Airworthiness 
Limitations List TRs AWL-75 and AWL-76, both dated July 14, 2000, or 
within 12 months after the effective date of this AD, whichever 
occurs later; according to de Havilland Inc. Dash 8 Series 100 
Maintenance Program Manual PSM 1-8-7. Thereafter, repeat the 
inspection at the applicable interval specified in the ``Initial 
Interval'' column of the table in TR AWL-75 and AWL -76, until the 
airplane reaches the applicable threshold listed in the ``Repeat 
Cut-In'' column of the table in TR AWL-75 and AWL-76. Thereafter, 
repeat the inspections at the applicable interval listed in the 
``Repeat Interval'' column of the table in TR AWL-75 and AWL -76, 
until paragraph (c) of this AD has been accomplished on all affected 
hook roller shafts. Where the TR specifies compliance intervals in 
``flights,'' for the purposes of this AD, ``flights'' means ``flight 
cycles.''
    (2) For Model DHC-8-200 series airplanes: For Pre Mod 8Q101103 
hook roller shafts having part number (P/N) 85750362-103 or 
85750362-105, do the initial inspection at the compliance time 
specified in the ``Threshold'' column of the table in de Havilland 
Inc. Airworthiness Limitations List TR AWL 2-19, dated July 14, 
2000, or within 12 months after the effective date of this AD, 
whichever occurs later; according to de Havilland Inc. Dash 8 Series 
200 Maintenance Program Manual PSM 1-82-7. Thereafter, repeat the 
inspection at the applicable interval specified in the ``Initial 
Interval'' column of the table in TR AWL 2-19, until the airplane 
reaches the applicable threshold listed in the ``Repeat Cut-In'' 
column of the table in TR AWL 2-19. Thereafter, repeat the 
inspections at the applicable interval listed in the ``Repeat 
Interval'' column of the table in TR AWL 2-19, until paragraph (c) 
of this AD has been accomplished on all affected hook roller shafts. 
Where the TR specifies compliance intervals in ``flights,'' for the 
purposes of this AD, ``flights'' means ``flight cycles.''
    (3) For Model DHC-8-300 series airplanes: For Pre Mod 8Q101103 
hook roller shafts having part number (P/N) 85750362-103 or 
85750362-105, do the initial inspection at the compliance time 
specified in the ``Threshold'' column of the table in de Havilland 
Inc. Airworthiness Limitations List TR AWL 3-83, or within 12 months 
after the effective date of this AD, whichever occurs later; 
according to de Havilland Inc. Dash 8 Series 300 Maintenance Program 
Manual PSM 1-83-7, dated July 14, 2000. Thereafter, repeat the 
inspection at the applicable interval specified in the ``Initial 
Interval'' column of the table in TR AWL 3-83, until the airplane 
reaches the applicable threshold listed in the ``Repeat Cut-In'' 
column of the table in TR AWL 3-83. Thereafter, repeat the 
inspections at the applicable interval listed in the ``Repeat 
Interval'' column of the table in TR AWL 3-83 until paragraph (c) of 
this AD has been accomplished on all affected hook roller shafts. 
Where the TR specifies compliance intervals in ``flights,'' for the 
purposes of this AD, ``flights'' means ``flight cycles.''

Replacement

    (c) At the applicable time specified in paragraph (c)(1) or 
(c)(2) of this AD, replace hook roller shafts having P/N 85750362-
103 or 85750362-105 with new or serviceable hook roller shafts 
having P/N 85750362-107, according to Sections 57-50-44 and 57-50-53 
of the de Havilland Inc. Dash 8 Aircraft Maintenance Manual, as 
applicable. Replacement of all hook roller shafts, P/N 85750362-103 
or 85750362-105, with new hook roller shafts, P/N 85750362-107, ends 
the repetitive inspections at the intervals required by paragraph 
(b) of this AD.
    (1) For hook roller shafts on which any corrosion or crack is 
found during any inspection per paragraph (b) of this AD: Do the 
replacement before further flight.
    (2) For uncracked or uncorroded hook roller shafts: Do the 
replacement within 20,000 flight cycles or 5 years after the 
effective date of this AD, whichever is first.

Post-Replacement Inspections

    (d) Following the replacement of hook roller shafts according to 
paragraph (c) of this AD, do the Structural Inspection Program for 
the hook roller shafts of the flap carriage, as specified in 
paragraph (d)(1), (d)(2), or (d)(3) of this AD, as applicable.
    (1) For Model DHC-8-100 series airplanes: Using the criteria for 
Mod 8Q101103 hook roller shafts having P/N 85750362-107, do the 
initial inspection at the compliance time specified in the 
``Threshold'' column of the table in de Havilland Inc. Airworthiness 
Limitations List TR AWL-75 and AWL ``76, both dated July 14, 2000, 
according to de Havilland Inc. Dash 8 Series 100 Maintenance Program 
Manual PSM 1-8-7. Thereafter, repeat the inspection at the 
applicable interval specified in the ``Initial Interval'' column of 
the table in TRs AWL-75 and AWL-76, until the airplane reaches the 
applicable threshold listed in the ``Repeat Cut-In'' column of the 
table in TRs AWL-75 and AWL-76. Thereafter, repeat the inspections 
at the applicable interval listed in the ``Repeat Interval'' column 
of the table in TRs AWL-75 and AWL-76. Where the TR specifies 
compliance intervals in ``flights,'' for the purposes of this AD, 
``flights'' means ``flight cycles.''
    (2) For Model DHC-8-200 series airplanes: Using the criteria for 
Mod 8Q101103 hook roller shafts having P/N 85750362-107, do the 
initial inspection at the compliance time specified in the 
``Threshold'' column of the table in de Havilland Inc. Airworthiness 
Limitations List TR AWL 2-19, dated July 14, 2000, according to de 
Havilland Inc. Dash 8 Series 200 Maintenance Program Manual PSM 1-
82-7. Thereafter, repeat the inspection at the applicable interval 
specified in the ``Initial Interval'' column of the table in TR AWL 
2-19, until the airplane reaches the applicable threshold listed in 
the ``Repeat Cut-In'' column of the table in TR AWL 2-19. 
Thereafter, repeat the inspections at the applicable interval listed 
in the ``Repeat Interval'' column of the table in TR AWL 2-19. Where 
the TR specifies compliance intervals in ``flights,'' for the 
purposes of this AD, ``flights'' means ``flight cycles.''
    (3) For Model DHC-8-300 series airplanes: Using the criteria for 
Mod 8Q101103 hook roller shafts having P/N 85750362-107, do the 
initial inspection at the compliance time specified in the 
``Threshold'' column of the table in de Havilland Inc. Airworthiness 
Limitations List TR AWL 3-83, dated July 14, 2000, according to de 
Havilland Inc. Dash 8 Series 300 Maintenance Program Manual PSM 1-
83-7. Thereafter, repeat the inspection at the applicable interval 
specified in the ``Initial Interval'' column of the table in TR AWL 
3-83, until the airplane reaches the applicable threshold listed in 
the ``Repeat Cut-In'' column of the table in TR AWL 3-83. 
Thereafter, repeat the inspections at the applicable interval listed 
in the ``Repeat Interval'' column of the table in TR AWL 3-83. Where 
the TR specifies compliance intervals in ``flights,'' for the 
purposes of this AD, ``flights'' means ``flight cycles.''

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, New York Aircraft Certification 
Office (ACO), FAA. 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.

    Note 3: Information concerning the existence of approved 
alternative methods of

[[Page 42992]]

compliance with this AD, if any, may be obtained from the New York 
ACO.

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.

Incorporation by Reference

    (g) The maintenance program manual revision shall be done in 
accordance with de Havilland Inc. Dash 8 Airworthiness Limitations 
List Temporary Revision AWL-75, dated July 14, 2000; de Havilland 
Inc. Dash 8 Airworthiness Limitations List Temporary Revision AWL-
76, dated July 14, 2000; de Havilland Inc. Airworthiness Limitations 
List Temporary Revision AWL 2-19, dated July 14, 2000; and de 
Havilland Inc. Airworthiness Limitations List Temporary Revision AWL 
3-83, dated July 14, 2000; as applicable. 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, 10 Fifth Street, Third Floor, Valley 
Stream, New York; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

    Note 4: The subject of this AD is addressed in Canadian 
airworthiness directive CF-1999-10R2, dated September 12, 2000.

Effective Date

    (h) This amendment becomes effective on July 31, 2002.

    Issued in Renton, Washington, on June 7, 2002.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-15367 Filed 6-25-02; 8:45 am]
BILLING CODE 4910-13-P