[Federal Register Volume 67, Number 20 (Wednesday, January 30, 2002)]
[Rules and Regulations]
[Pages 4342-4344]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-1962]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-112-AD; Amendment 39-12620; AD 2002-01-25]
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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[[Page 4343]]

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Bombardier Model DHC-8-100, -200, and -300 series 
airplanes, that requires repetitive inspections of the rudder pedal 
adjustment fittings for cracks and replacement of cracked fittings with 
new fittings. This amendment also provides an optional terminating 
action. This action is necessary to detect and correct cracking of the 
rudder pedal adjustment fittings, which could lead to deformation of 
the fittings, resulting in jammed rudder pedals and loss of rudder 
control, with consequent reduced controllability of the airplane. This 
action is intended to address the identified unsafe condition.

DATES: Effective March 6, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 6, 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, 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 August 29, 2001 (66 FR 45653). That action proposed to 
require repetitive inspections of the rudder pedal adjustment fittings 
for cracks and replacement of cracked fittings with new fittings. That 
action also proposed to provide an optional terminating action.

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 Changes Made to Proposed AD

    The FAA has added a note, Note 2, to the final rule to clarify the 
definition of the detailed visual inspection required by paragraph (a) 
of this AD. Subsequent notes have been renumbered accordingly.
    Also, we have changed paragraph (c) of this AD to clarify that only 
``cracked'' fittings are required to be replaced.

Clarification of Terminating Action

    Since the issuance of the notice of proposed rulemaking (NPRM), the 
FAA has also determined that the optional terminating action specified 
in paragraph (d) of the NPRM needs to be clarified. That paragraph 
states, ``Replacement of the rudder pedal adjustment fittings having P/
N 82710038-101, with steel rudder pedal adjustment fittings having P/N 
82710080-101, constitutes terminating action for the repetitive 
inspections required by paragraphs (a) and (b) of this AD.'' However, 
the inspection required by paragraph (a) of this AD is not a repetitive 
inspection. Additionally, it was our intent that operators may elect to 
accomplish the replacement in lieu of the inspections required by 
paragraphs (a) and (b) of this AD. Therefore, we have revised paragraph 
(d) of the final rule to state, ``Replacement of rudder pedal 
adjustment fittings having P/N 82710038-101, with steel rudder pedal 
adjustment fittings having P/N 82710080-101, constitutes terminating 
action for the requirements of this 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 changes described previously. The FAA has determined that 
these changes will neither increase the economic burden on any operator 
nor increase the scope of the AD.

Cost Impact

    The FAA estimates that 188 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 1 work hour per 
airplane to accomplish the required inspection, and that the average 
labor rate is $60 per work hour. Based on these figures, the cost 
impact of the AD on U.S. operators is estimated to be $11,280, or $60 
per airplane, per inspection cycle.
    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 
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.

[[Page 4344]]

Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2002-01-25  Bombardier, Inc. (Formerly de Havilland, Inc.): 
Amendment 39-12620. Docket 2001-NM-112-AD.

    Applicability: Model DHC-8-100, -200, and -300 series airplanes, 
serial numbers 003 to 563 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 detect and correct cracking of the rudder pedal adjustment 
fittings, which could lead to deformation of the fittings, resulting 
in jammed rudder pedals and loss of rudder control, with consequent 
reduced controllability of the airplane, accomplish the following:

Inspections

    (a) Perform a detailed visual inspection of the rudder pedal 
adjustment fittings having part number (P/N) 82710038-101 for 
cracks, in accordance with Bombardier Alert Service Bulletin A8-27-
91, dated September 12, 2000, or Revision A, dated November 23, 
2000, at the times specified in paragraphs (a)(1) and (a)(2) of this 
AD.
    (1) Within 5,000 flight hours since the date of manufacture of 
the airplane or 500 flight hours after the effective date of this 
AD, whichever occurs later; and
    (2) Prior to further flight, whenever an instance of stiff 
operation or jamming of the rudder pedals occurs during flight.

    Note 2: For the purposes of this AD, a detailed visual 
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) If no crack is detected: Repeat the inspection of the rudder 
pedal adjustment fittings having P/N 82710038-101, in accordance 
with Bombardier Alert Service Bulletin A8-27-91, dated September 12, 
2000, or Revision A, dated November 23, 2000, at intervals not to 
exceed 1,000 flight hours, until accomplishment of paragraph (d) of 
this AD.

Replacement

    (c) If any crack is detected: Prior to further flight, replace 
the cracked rudder pedal adjustment fitting having P/N 82710038-101 
with a new aluminum fitting having the same P/N (82710038-101), or 
with a steel fitting having P/N 82710080-101, in accordance with 
Bombardier Alert Service Bulletin A8-27-91, dated September 12, 
2000, or Revision A, dated November 23, 2000.

Terminating Action

    (d) Replacement of rudder pedal adjustment fittings having P/N 
82710038-101, with steel rudder pedal adjustment fittings having P/N 
82710080-101, constitutes terminating action for the requirements of 
this AD.

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, 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 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 actions shall be done in accordance with Bombardier 
Alert Service Bulletin A8-27-91, dated September 12, 2000; or 
Bombardier Alert Service Bulletin A8-27-91, Revision A, dated 
November 23, 2000. 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-2001-04, dated January 25, 2001.

Effective Date

    (h) This amendment becomes effective on March 6, 2002.

    Issued in Renton, Washington, on January 18, 2002.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-1962 Filed 1-29-02; 8:45 am]
BILLING CODE 4910-13-U