[Federal Register Volume 66, Number 166 (Monday, August 27, 2001)]
[Rules and Regulations]
[Pages 44958-44960]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-21490]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-45-AD; Amendment 39-12301; AD 2001-13-19]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106, 
-201, -202, -301, -311, -314, and -315 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; correction.

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SUMMARY: This document corrects information in an existing 
airworthiness directive (AD) that applies to all Bombardier Model DHC-
8-102, -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 CF-2000-07, dated March 3, 2000, and 
de Havilland Temporary Revision TR AWL 2-15, dated September 3, 1999.

[[Page 44959]]


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).

FOR FURTHER INFORMATION CONTACT: Serge Napoleon, Aerospace Engineer, 
ANE-171, FAA, 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 June 26, 2001, the Federal Aviation 
Administration (FAA) issued AD 2001-13-19, amendment 39-12301 (66 FR 
35538, July 6, 2001), which applies to all Bombardier Model DHC-8-102, 
-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 2001-13-19, 
contains an error in referencing certain airplane models for the 
effectivity of de Havilland Temporary Revision TR AWL 2-15, dated 
September 3, 1999. Our intent was to specify the airplane models 
referenced in TR AWL 2-15 as only Models DHC-8-201 and -202 series 
airplanes. We also note that Canadian airworthiness directive CF-2000-
07, dated March 3, 2000, as referenced in AD 2001-13-19, specifies only 
Model DHC-8-201 and -202 series airplanes for the effectivity of TR AWL 
2-15. 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 CF-2000-07 and TR AWL 2-15, 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 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  [Corrected]

    2. Section 39.13 is amended by correctly adding the following 
airworthiness directive (AD):

2001-13-19  Bombardier, Inc. (Formerly de Havilland, Inc.): 
Amendment 39-12301. Docket 2000-NM-45-AD.

    Applicability: Model DHC-8-102, -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 DHC-8 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
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           Bombardier models                             TR Number                              Date
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DHC-8-102, -103, and -106 series         TR AWL-71                                  September 3, 1999.
 airplanes.
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DHC-8-201 and -202 series airplanes....  TR AWL 2-15                                September 3, 1999.
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DHC-8-301, -311, -314, and -315 series   TR AWL 3-78                                November 19, 1999.
 airplanes.
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    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 
DHC-8 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 
AWL-71, dated September 3, 1999; de Havilland Temporary Revision TR 
AWL 2-15, dated September 3, 1999; and de Havilland Temporary 
Revision TR AWL 3-78, 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 CF-2000-07, 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. 01-21490 Filed 8-24-01; 8:45 am]
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