[Federal Register Volume 61, Number 225 (Wednesday, November 20, 1996)]
[Rules and Regulations]
[Pages 58983-58985]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-29416]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-163-AD; Amendment 39-9822; AD 96-23-17]
RIN 2120-AA64


Airworthiness Directives; de Havilland Model DHC-8-102 and-103 
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 de Havilland Model DHC-8-102 and -103 series 
airplanes, that requires repetitive external inspections to detect 
cracks in the skin exterior of the fuselage at floor level, and repair, 
if necessary. This amendment also requires repetitive internal 
inspections to detect cracks of the subject area, which terminates the 
repetitive external inspections. This amendment is prompted by a report 
that one of the tasks in the Maintenance Program Airworthiness 
Limitations List inadvertently excluded certain airplanes from the 
instructions for the

[[Page 58984]]

inspections. The actions specified by this AD are intended to prevent 
undetected cracking of the frames and skin panels of the fuselage, 
which could result in reduced structural integrity of the airplane.

DATES: Effective December 26, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 26, 1996.

ADDRESSES: The service information referenced in this AD may be 
obtained from Bombardier, Inc., Bombardier Regional Aircraft Division, 
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, 
Engine and Propeller Directorate, 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: Jon Hjelm, Aerospace Engineer, Systems 
and Equipment Branch, ANE-172, FAA, New York Aircraft Certification 
Office, Engine and Propeller Directorate, 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) to include an airworthiness 
directive (AD) that is applicable to certain de Havilland Model DHC-8-
102 and-103 series airplanes was published in the Federal Register on 
August 30, 1996 (61 FR 45914). That action proposed to require 
repetitive external detailed visual inspections to detect cracks in the 
left-and right-hand skin exterior of the fuselage at the floor level. 
That action also proposed to require repetitive internal visual 
inspections to detect cracks of the fuselage frames; initiation of 
these inspections would constitute terminating action for the 
repetitive external inspection requirements.
    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 80 de Havilland Model DHC-8-102 and-103 
series airplanes of U.S. registry will be affected by this AD.
    The required external inspections will take approximately 1 work 
hour per airplane to accomplish, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of the AD on U.S. 
operators is estimated to be $4,800, or $60 per airplane, per 
inspection.
    The required internal inspections will take approximately 3 work 
hours per airplane to accomplish, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of the AD on U.S. 
operators is estimated to be $14,400, or $180 per airplane, per 
inspection.
    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.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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:

96-23-17 De Havilland, Inc.: Amendment 39-9822. Docket 95-NM-163-AD.

    Applicability: Model DHC-8-102 and -103 series airplanes having 
serial numbers 101 through 180, inclusive; on which de Havilland 
Modification 8/0427 has been installed, and on which Maintenance 
Program Manual PSM 1-8-7, Task 5310/30C (Section 3-53, page 12, 
dated August 10,1993) has not been accomplished; certificated in any 
category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 (c) 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 undetected cracking of the frames and skin panels of 
the fuselage, which could result in reduced structural integrity of 
the airplane, accomplish the following:
    (a) Prior to the accumulation of 15,343 total flight cycles, or 
within 200 landings after the effective date of this AD, whichever 
occurs later, perform an external detailed visual inspection to 
detect cracks in the left-and right-hand skin exterior of the 
fuselage at floor level, in accordance with paragraph III, External 
Inspection, of the Accomplishment Instructions of de Havilland 
Service Bulletin S.B. 8-53-48, dated August 26, 1994.
    (1) If no crack is detected, repeat the external detailed visual 
inspection thereafter at intervals not to exceed 750 landings.
    (2) If any crack is detected, prior to further flight, perform 
an internal visual inspection to detect cracks of the fuselage 
frames in accordance with the service bulletin. Accomplishment of 
this internal visual inspection constitutes terminating action for 
the repetitive external detailed visual inspections required by of 
paragraph (a)(1) of this AD.
    (i) If no crack is detected during the internal inspection, 
prior to further flight, repair the cracked area(s) found during the

[[Page 58985]]

external inspection, in accordance with the de Havilland DHC-8 
Structural Repair Manual; or in accordance with a method approved by 
Transport Canada; or in accordance with a method approved by the 
Manager, New York Aircraft Certification Office (ACO), FAA, Engine 
and Propeller Directorate. Repeat the internal inspection thereafter 
at intervals specified in accordance with the Dash 8 Maintenance 
Program Manual.
    (ii) If any crack is detected during the internal inspection, 
prior to further flight, repair all cracks found during both the 
external and internal inspections, in accordance with the de 
Havilland DHC-8 Structural Repair Manual, or in accordance with a 
method approved by Transport Canada Aviation; or in accordance with 
a method approved by the Manager, New York ACO, FAA, Engine and 
Propeller Directorate. Repeat the internal inspection thereafter at 
intervals specified in accordance with the Dash 8 Maintenance 
Program Manual.
    (b) Prior to the accumulation of 31,000 flight cycles, or within 
12 months after the effective date of this AD, whichever occurs 
later, perform an internal visual inspection to detect cracking of 
the fuselage frames, in accordance with de Havilland Service 
Bulletin S.B. 8-53-48, dated August 26, 1994. Accomplishment of the 
internal visual inspection constitutes terminating action for the 
repetitive external detailed visual inspections required by 
paragraph (a)(1) of this AD.
    (1) If no cracking is detected during the internal inspection, 
repeat the internal inspection thereafter at intervals specified in 
accordance with the Dash 8 Maintenance Program Manual.
    (2) If any cracking is detected during the internal inspection, 
prior to further flight, repair it in accordance with the de 
Havilland DHC-8 Structural Repair Manual, or in accordance with a 
method approved by Transport Canada Aviation; or in accordance with 
a method approved by the Manager, New York ACO, FAA, Engine and 
Propeller Directorate. Repeat the internal inspection thereafter at 
intervals specified in accordance with the Dash 8 Maintenance 
Program Manual.
    (c) 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 (ACO), FAA, Engine and Propeller Directorate. 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.
    (d) 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.
    (e) The inspections shall be done in accordance with de 
Havilland Service Bulletin S.B. 8-53-48, dated August 26, 1994. 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, 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, Engine and 
Propeller Directorate, 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.
    (f) This amendment becomes effective on December 26, 1996.

    Issued in Renton, Washington, on November 8, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-29416 Filed 11-19-96; 8:45 am]
BILLING CODE 4910-13-U