[Federal Register: January 26, 2004 (Volume 69, Number 16)]
[CORRECTIONS]
[Page 3629]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26ja04-93]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-266-AD; Amendment 39-13388; AD 2003-25-05]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and
-315 Airplanes
Correction
In rule document 03-31058 beginning on page 70428 in the issue of Thursday, December 18,
2003 make the following correction:
§ 39.13 [Corrected]
On page 70429, in § 39.13, in the second column, under paragragh (a)(2), in the last line, ''exceed
50 flight hours'' should read, ''exceed 500 flight hours ''.
[FR Doc. C3-31058 Filed 1-23-04; 8:45 am]
BILLING CODE 1505-01-D
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[Federal Register: December 18, 2003 (Volume 68, Number 243)]
[Rules and Regulations]
[Page 70428-70429]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18de03-4]
–––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-266-AD; Amendment 39-13388; AD 2003-25-05]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and
-315 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
–––––––––––––––––––––––––––––––––––
SUMMARY: This amendment supersedes an existing airworthiness directive (AD), applicable to
certain Bombardier DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 airplanes, that currently
requires inspections to detect breakage in the struts of the rear mount strut assemblies on the left and
right engine nacelles, and replacement of any broken struts. The existing AD also requires eventual
replacement of all currently installed struts with new and/or reworked struts, as terminating action for
the inspections. The amendment requires new repetitive inspections of the strut assemblies for
cracking of struts replaced per the existing AD, and replacement of any cracked strut with a new,
machined strut. The amendment also changes the applicability of the existing AD by adding certain
airplanes and removing certain other airplanes, and includes an optional terminating action for the
repetitive inspections. The actions specified by this AD are intended to prevent failure of the engine
rear mount struts, which could result in reduced structural integrity of the nacelle and engine support
structure. This action is intended to address the identified unsafe conditions.
DATES: Effective January 22, 2004.
The incorporation by reference of certain publications listed in the regulations is approved by the
Director of the Federal Register as of January 22, 2004.
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.
2
FOR FURTHER INFORMATION CONTACT: Jon Hjelm, Aerospace Engineer, Airframe
Branch, ANE-171, FAA, New York Aircraft Certification Office, 10 Fifth Street, Third Floor, Valley
Stream, New York 11581; telephone (516) 256-7523; fax (516) 568-2716.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation
Regulations (14 CFR part 39) by superseding AD 94-04-09, amendment 39-8829 (59 FR 8393,
February 22, 1994), which is applicable to certain Bombardier Model DHC-8-100 and DHC-8-300
airplanes, was published in the Federal Register on October 9, 2003 (68 FR 58283). The action
proposed to require new repetitive inspections of the strut assemblies for cracking of struts replaced
per the existing AD, and replacement of any cracked strut with a new, machined strut. The action also
proposed to change the applicability of the existing AD by adding certain airplanes and removing
certain other airplanes, and proposed to include an optional terminating action 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.
Conclusion
The FAA has determined that air safety and the public interest require the adoption of the rule as
proposed.
Cost Impact
There are approximately 192 airplanes of U.S. registry that will be affected by this AD.
The actions that are currently required by AD 94-04-09 take approximately 16 work hours per
airplane to accomplish, at an average labor rate of $65 per work hour. Required parts are provided by
the manufacturer at no cost to the operators. Based on these figures, the cost impact of the currently
required actions is estimated to be $1,040 per airplane.
The new detailed inspection that is required in this AD action takes approximately 1 work hour
per airplane to accomplish, at an average labor rate of $65 per work hour. Based on these figures, the
cost impact of the required inspection on U.S. operators is estimated to be $12,480, or $65 per
airplane, per inspection cycle.
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.
The optional terminating action, if done, will take approximately 16 work hours per strut to
accomplish, at an average labor rate of $65 per work hour. Required parts will cost aproxiamately
$800 per strut. Based on these figures, the cost impact of the optional terminating action is estimated
to be $1,840 per strut, per airplane.
3
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 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.
§ 39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-8829 (59 FR 8393, February 22, 1994), and
by adding a new airworthiness directive (AD), amendment 39-13388, to read as follows:
4
AIRWORTHINESS DIRECTIVE
Aircraft Certification Service U.S. Department
Washington, DC of Transportation
Federal Aviation
Administration
We post ADs on the internet at "www.faa.gov"
The following Airworthiness Directive issued by the Federal Aviation Administration in accordance with the provisions of Title 14 of the Code of Federal Regulations (14 CFR) part 39,
applies to an aircraft model of which our records indicate you may be the registered owner. Airworthiness Directives affect aviation safety and are regulations which require immediate
attention. You are cautioned that no person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of the Airworthiness
Directive (reference 14 CFR part 39, subpart 39.3).
CORRECTION: [Federal Register: January 26, 2004 (Volume 69, Number 16); Page 3629;
www.access.gpo.gov/su_docs/aces/aces140.html]
2003-25-05 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 39-13388. Docket 2001-
NM-266-AD. Supersedes AD 94-04-09, Amendment 39-8829.
Applicability: Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 airplanes; serial
numbers 003 through 509 inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent failure of the engine rear mount struts on the left and right engine nacelles, which
could result in reduced structural integrity of the nacelle and engine support structure, accomplish the
following:
Repetitive Inspections
(a) Within 1,000 flight hours since installation of any new or reworked rear mount strut per the
replacement required by paragraph (b) of AD 94-04-09, amendment 39-8829, or within 250 flight
hours after the effective date of this AD, whichever is later; do a detailed inspection for cracking of
each rear mount strut in the left and right engine nacelles.
Note 1: Bombardier Service Bulletin 8-71-24, dated August 21, 2001, does not contain
inspection procedures for the detailed inspection required by paragraph (a) of this AD; however, the
definition of a detailed inspection is specified in Note 2 of this AD.
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) If no crack is found, repeat the inspection at intervals not to exceed 250 flight hours, until
accomplishment of paragraph (b) of this AD.
(2) If any crack is found, before further flight, replace the strut with a new, improved strut per
Bombardier Service Bulletin 8-71-24, dated August 21, 2001. Repeat the inspection thereafter at
intervals not to exceed 500 flight hours, for that nacelle only.
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Optional Terminating Action
(b) Replacement of both rear mount struts in a nacelle with new, improved struts, by doing all
the actions specified in the Job Set-up, Procedure, and Close-out sections of the Accomplishment
Instructions of Bombardier Service Bulletin 8-71-24, dated August 21, 2001, ends the repetitive
inspections required by this AD for that nacelle only. Replacement of both rear mount struts on both
the left and right engine nacelles ends the repetitive inspections required by this AD.
Parts Installation
(c) As of the effective date of this AD, no person shall install an engine rear mount strut, P/N
87110016-001, -003, -005, -007, -009, or -011, on any airplane.
Alternative Methods of Compliance
In accordance with 14 CFR 39.19, the Manager, New York Aircraft Certification Office, FAA, is
authorized to approve alternative methods of compliance for this AD.
Incorporation by Reference
(e) Unless otherwise provided in this AD, the actions shall be done in accordance with
Bombardier Service Bulletin 8-71-24, dated August 21, 2001. This incorporation by reference was
approved by the Director of the Federal Register in accordance with 5 U.S.C. 522(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 3: The subject of this AD is addressed in Canadian airworthiness directive CF-2001-20,
dated May 16, 2001.
Effective Date
(f) This amendment becomes effective on January 22, 2004.
Issued in Renton, Washington, on December 5, 2003.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-31058 Filed 12-17-03; 8:45 am]
BILLING CODE 4910-13-M
