AD 2000-11-20

[Federal Register Volume 65, Number 114 (Tuesday, June 13, 2000)]
[Rules and Regulations]
[Pages 37014-37015]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-14313]



[[Page 37014]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-380-AD; Amendment 39-11768; AD 2000-11-20]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-100 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 and -300 series 
airplanes, that requires revising the Aircraft Log Book to correct the 
airplane Production Modification List; performing an inspection to 
determine which bonded skin panels on the airplane require bonding 
integrity inspections (BII); and revising the Airworthiness Limitations 
List of the Approved Maintenance Plan to include the BII requirements. 
This amendment also requires, for certain airplanes, repetitive 
ultrasonic bond inspections to detect disbonding of airplane skin 
panels, and repair, if necessary. This amendment is prompted by 
issuance of mandatory continuing airworthiness information by a foreign 
civil airworthiness authority. The actions specified by this AD are 
intended to prevent damage to bonded skin panels to go undetected, 
which could result in failure of the bonded skin panels, and consequent 
loss of controllability of the airplane.

DATES: Effective July 18, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 18, 2000.

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, Engine and Propeller 
Directorate, 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: Franco Pieri, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, Engine and Propeller 
Directorate, New York Aircraft Certification Office, 10 Fifth Street, 
Third Floor, Valley Stream, New York 11581; telephone (516) 256-7526; 
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 
and -300 series airplanes was published in the Federal Register on 
March 31, 2000 (65 FR 17206). That action proposed to require revising 
the Aircraft Log Book to correct the airplane Production Modification 
List; performing an inspection to determine which bonded skin panels on 
the airplane require bonding integrity inspections (BII); and revising 
the Airworthiness Limitations List of the Approved Maintenance Plan to 
include the BII requirements. That action also proposed to require, for 
certain airplanes, repetitive ultrasonic bond inspections to detect 
disbonding of airplane skin panels, and repair, if necessary.

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

    The FAA estimates that 41 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 revisions to the Aircraft Log Book, 
Approved Maintenance Plan, and inspection, and that the average labor 
rate is $60 per work hour. Based on these figures, the cost impact of 
the actions required by this AD on U.S. operators is estimated to be 
$2,460, or $60 per airplane.
    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.

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:

2000-11-20  Bombardier Inc. (Formerly de Havilland, Inc.): Amendment 
39-11768. Docket 98-NM-380-AD.

    Applicability: Model DHC-8-100 and -300 series airplanes, serial 
numbers 215 through 341 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

[[Page 37015]]

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 damage to bonded skin panels to go undetected, which 
could result in failure of the bonded skin panels, and consequent 
loss of controllability of the airplane, accomplish the following:

Revision to Aircraft Log Book and Airworthiness Limitations List

    (a) Within 30 days after the effective date of this AD, perform 
the actions required by paragraphs (a)(1), (a)(2), and (a)(3) of 
this AD.
    (1) Revise the Aircraft Log Book to correct the airplane 
Production Modification List in accordance with the Accomplishment 
Instructions in Part A of Section III of Bombardier Service Bulletin 
S.B. 8-51-2, Revision `A,' dated September 19, 1998.
    (2) Perform an inspection to determine which bonded skin panels 
on the airplane require bonding integrity inspections (BII) in 
accordance with the Accomplishment Instructions in Part B of Section 
III of Bombardier Service Bulletin S.B. 8-51-2, Revision `A,' dated 
September 19, 1998.
    (3) Revise the Airworthiness Limitations List of the Approved 
Maintenance Plan by inserting the bonding integrity inspections 
identified as de Havilland Maintenance Task 5500/01 and de Havilland 
Maintenance Task 5700/01 into the Airworthiness Limitations List. 
Except as provided by paragraph (e) of this AD: After the actions 
specified in paragraph (a)(3) of this AD have been accomplished, no 
alternative replacement times or structural inspection intervals may 
be approved for the bonded panels of the empennage and wings 
specified in de Havilland Maintenance Task 5500/01 and de Havilland 
Maintenance Task 5700/01.

On-Condition Repetitive Inspections

    (b) For airplanes on which the bonded skin panels require BII's, 
as determined in paragraph (a)(2) of this AD: At the next required 
maintenance visit, but no later than 12 months after the effective 
date of this AD, perform an initial ultrasonic bond inspection to 
detect disbonding of the skin panels, in accordance with Part 5, 
sections 55-00-01 and/or 57-30-01, of Bombardier Production Support 
Manual (PSM) 1-8-7A, dated December 15, 1998 (for Model DHC-8-100 
series airplanes); or Part 5, sections 55-00-01 and 57-30-01 of 
Bombardier PSM 1-83-7A, dated April 30, 1999 (for Model DHC-8-300 
series airplanes); as applicable. Thereafter, repeat the ultrasonic 
inspection at the interval specified in the applicable PSM.

On-Condition Repair

    (c) Except as provided by paragraph (d) of this AD, if any 
disbonding is detected during any inspection required by paragraph 
(b) of this AD, prior to further flight, repair in accordance with 
Part 5, sections 55-00-01 and 57-30-01 of Bombardier PSM 1-8-7A, 
dated December 15, 1998 (for Model DHC-8-100 series airplanes); or 
Part 5, sections 55-00-01 and 57-30-01 of Bombardier PSM 1-83-7A, 
dated April 30, 1999 (for Model DHC-8-300 series airplanes); as 
applicable.
    (d) If any disbonding is detected during any inspection required 
by paragraph (b) of this AD; and the applicable service information 
specifies to contact Bombardier for appropriate action: Prior to 
further flight, repair in accordance with a method approved by the 
Manager, New York Aircraft Certification Office (ACO), FAA, Engine 
and Propeller Directorate. For a repair 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.

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 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 2:
    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 
Secs. 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 Aircraft Log Book revision required by paragraph (a)(1) 
and the inspection required by paragraph (a)(2) of this AD shall be 
done in accordance with Bombardier Service Bulletin S.B. 8-51-2, 
Revision `A,' dated September 19, 1998. 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, Engine and 
Propeller Directorate, 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-98-31, dated September 1, 1998.

    (h) This amendment becomes effective on July 18, 2000.

    Issued in Renton, Washington, on June 1, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-14313 Filed 6-12-00; 8:45 am]
BILLING CODE 4910-13-U