Federal Register: August 27, 2001 (Volume 66, Number 166)
DOCID: FR Doc 01-21490
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
CFR Citation: 14 CFR Part 39
Docket ID: [Docket No. 2000-NM-45-AD; Amendment 39-12301; AD 2001-13-19]
RIN ID: RIN 2120-AA64
NOTICE: RULES
ACTION: Airworthiness directives:
DOCUMENT ACTION: Final rule; correction.
SUBJECT CATEGORY:
Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, -314, and -315 Series Airplanes
DATES: Effective August 10, 2001.
The incorporation by reference of certain publications listed in the regulations was approved previously by the Director of the Federal Register as of August 10, 2001 (66 FR 35538, July 6, 2001).
DOCUMENT SUMMARY:
This document corrects information in an existing
airworthiness directive (AD) that applies to all Bombardier Model DHC 8102, 103, 106, 201, 202, 301, 311, 314, and 315 series
airplanes. That AD currently requires revising the Bombardier
maintenance program to incorporate repetitive inspections to detect
fatigue cracking in certain structures; and corrective actions, if
necessary. This document corrects certain airplane models specified in
Table 1 of the final rule. This correction is necessary to ensure that
operators are notified of the correct airplane models, as specified in
Canadian airworthiness directive CF200007, dated March 3, 2000, and
de Havilland Temporary Revision TR AWL 215, dated September 3, 1999.
[[Page 44959]]
SUMMARY:
Bombardier; correction,
SUPPLEMENTAL INFORMATION
On June 26, 2001, the Federal Aviation Administration (FAA) issued AD 20011319, amendment 3912301 (66 FR 35538, July 6, 2001), which applies to all Bombardier Model DHC8102, 103, 106, 201, 202, 301, 311, 314, and 315 series airplanes. That AD requires revising the Bombardier maintenance program to incorporate repetitive inspections to detect fatigue cracking in certain structures; and corrective actions, if necessary. That AD was prompted by issuance of mandatory continuing airworthiness information issued by a foreign airworthiness authority. The actions required by that AD are intended to ensure that fatigue cracking of certain principal structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
Need for the Correction
The FAA notes that paragraph (a)(1), Table 1, of AD 20011319, contains an error in referencing certain airplane models for the effectivity of de Havilland Temporary Revision TR AWL 215, dated September 3, 1999. Our intent was to specify the airplane models referenced in TR AWL 215 as only Models DHC8201 and 202 series airplanes. We also note that Canadian airworthiness directive CF2000 07, dated March 3, 2000, as referenced in AD 20011319, specifies only Model DHC8201 and 202 series airplanes for the effectivity of TR AWL 215. We have revised Table 1 of this AD accordingly.
The FAA has determined that the correction to Table 1 in paragraph (a)(1) of this AD is necessary. The correction will ensure that operators are notified of the correct airplane models that must be inspected, as required by this AD.
Correction of Publication
This document corrects the error and correctly adds the AD as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13).
The AD is reprinted in its entirety for the convenience of affected operators. The effective date of the AD remains August 10, 2001.
Since this action only corrects the airplane models as specified by Canadian airworthiness directive CF200007 and TR AWL 215, it has no adverse economic impact and imposes no additional burden on any person. Therefore, the FAA has determined that notice and public procedures are unnecessary.
List of Subject in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Correction
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 39AIRWORTHINESS 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 [Corrected]
2. Section 39.13 is amended by correctly adding the following airworthiness directive (AD):
20011319 Bombardier, Inc. (Formerly de Havilland, Inc.):
Amendment 3912301. Docket 2000NM45AD.
Applicability: Model DHC8102, 103, 106, 201, 202, 301, 311, 314, and 315 series airplanes, 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 (d) 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 ensure continued structural integrity of these airplanes, accomplish the following:
(a) Within 30 days after the effective date of this AD,
accomplish the actions required by either paragraph (a)(1) or (a)(2) of this AD, as applicable.
Maintenance Program Revisions
(1) Revise the Bombardier maintenance program by incorporating
the threshold and repetitive inspection intervals specified in the
Temporary Revisions (TR's) to the DHC8 Maintenance Program Manuals,
Airworthiness Limitations List (AWL), Structural Inspection Program
Task No. 5310/31A, into the Bombardier maintenance program. The TR's
for specific airplane models are listed in Table 1, as follows:
Table 1.List of Temporary Revisions
Bombardier models TR Number Date
DHC8102, 103, and 106 series TR AWL71 September 3, 1999. airplanes.
DHC8201 and 202 series airplanes.... TR AWL 215 September 3, 1999.
DHC8301, 311, 314, and 315 series TR AWL 378 November 19, 1999. airplanes.
Note 2: When the TR documents listed in Table 1 in paragraph
(a)(1) of this AD are incorporated into the general revisions of the
DHC8 Maintenance Program Manual, you may insert the general
revisions into the Bombardier maintenance program, provided that the
information contained in the general revisions is identical to that specified in the TR documents.
Structural Inspections
(2) For airplanes having closing angles that are identified as
principal structural elements: Do the inspections specified by the
applicable TR listed in Table 1 of paragraph (a) of this AD.
Thereafter, repeat the inspection at intervals not to exceed 10,000
flight cycles at the time specified in paragraph (a)(2)(i), (a)(2)(ii), or (a)(2)(iii) of this AD, as applicable.
(i) For airplanes that have accumulated less than 8,000 flight
cycles as of the effective date of this AD: Do the threshold inspection
[[Page 44960]]
prior to the accomplishment of 10,000 flight cycles, or within 2,000
flight cycles after the effective date of this AD, whichever occurs later.
(ii) For airplanes that have accumulated 8,000 flight cycles or
more as of the effective date of this AD: Do the threshold
inspection within 2,000 flight cycles after the effective date of this AD.
(iii) For airplanes on which a 40,000 flight cycle inspection
specified by the applicable TR listed in Table 1 of paragraph (a) of
this AD has been done: Start the 10,000 flight cycle repetitive
inspection at the time specified by paragraph (a)(2)(iii)(A) or (a)(2)(iii)(B) of this AD, as applicable.
(A) If no cracks were found, start the cycle from the date of the 40,000 flight cycle inspection.
(B) If cracks have been found and the closing angles have been
replaced as provided in paragraph (b) of this AD, start the cycle from the date of the replacement.
Corrective Actions
(b) If any crack is detected during any structural inspection
required by paragraph (a)(2) of this AD, before further flight,
repair any such cracking or replace the closing angles per a method
approved by the Manager, New York Aircraft Certification Office
(ACO), FAA; or the Transport Canada Civil Aviation (or its delegated
agent). For a repair or replacement method to be approved by the
Manager, New York ACO, as required by this paragraph, the Manager's approval letter must specifically reference this AD.
(c) Except as provided by paragraph (d) of this AD: After the
actions specified in paragraphs (a) and (b) of this AD have been
accomplished, no alternative inspections or inspection intervals may
be approved for the structural elements specified by the documents listed in Table 1 of paragraph (a)(1) of this AD.
Alternative Methods of Compliance
(d) 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.
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
(e) 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
(f) Except as provided in paragraph (b) of this AD, the actions
shall be done in accordance with de Havilland Temporary Revision TR
AWL71, dated September 3, 1999; de Havilland Temporary Revision TR
AWL 215, dated September 3, 1999; and de Havilland Temporary
Revision TR AWL 378, dated November 19, 1999. This incorporation by
reference was approved previously by the Director of the Federal
Register as of August 10, 2001. 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 ACO, 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 CF200007, dated March 3, 2000.
Effective Date
(g) The effective date of this amendment remains August 10, 2001.
Issued in Renton, Washington, on August 20, 2001. Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 0121490 Filed 82401; 8:45 am]
BILLING CODE 491013P
FOR FURTHER INFORMATION CONTACT
Serge Napoleon, Aerospace Engineer, ANE171, FAA, New York Aircraft Certification Office, 10 Fifth Street, Third Floor, Valley Stream, New York 11581; telephone (516) 2567512; fax (516) 5682716.