[Federal Register Volume 64, Number 139 (Wednesday, July 21, 1999)]
[Rules and Regulations]
[Pages 39001-39003]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-18197]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-CE-05-AD; Amendment 39-11226; AD 99-15-07]
RIN 2120-AA64


Airworthiness Directives; deHavilland Inc. Models DHC-2 Mk. I, 
DHC-2 Mk. II, and DHC-2 Mk. III Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to all deHavilland Inc. (deHavilland) Models DHC-2 Mk. I, DHC-2 
Mk. II, and DHC-2 Mk. III airplanes. This AD requires repetitively 
inspecting the rear fuselage bulkhead at Station 228 for cracks. This 
AD also requires repairing any crack found or replacing any cracked 
rear fuselage bulkhead in accordance with a repair or replacement 
scheme obtained from the manufacturer through the Federal Aviation 
Administration (FAA). This AD is the result of mandatory continuing 
airworthiness information (MCAI) issued by the airworthiness authority 
for Canada. The actions specified by this AD are intended to detect and 
correct cracking of the rear fuselage bulkhead at Station 228, which 
could result in structural damage of the fuselage to the point of 
failure with consequent loss of airplane control.

DATES: Effective September 10, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 10, 1999.

ADDRESSES: Service information that applies to this AD may be obtained 
from Bombardier Inc., Bombardier Regional Aircraft Division, Garratt 
Boulevard, Downsview, Ontario, Canada M3K 1Y5; telephone: (416) 633-
7310. This information may also be examined at the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules

[[Page 39002]]

Docket No. 99-CE-05-AD, Room 1558, 601 E. 12th Street, Kansas City, 
Missouri 64106; or at the Office of the Federal Register, 800 North 
Capitol Street, NW, suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr. James Delisio, Aerospace Engineer, 
FAA, New York Aircraft Certification Office, 10 Fifth Street, 3rd 
Floor, Valley Stream, New York 11581-1200; telephone: (516) 256-7521; 
facsimile: (516) 568-2716.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This AD

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to all deHavilland 
Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III airplanes was 
published in the Federal Register as a notice of proposed rulemaking 
(NPRM) on April 23, 1999 (64 FR 19932). The NPRM proposed to require 
repetitively inspecting the rear fuselage bulkhead at Station 228 for 
cracks. Accomplishment of the proposed repetitive inspections as 
specified in the NPRM would be required in accordance with deHavilland 
Beaver Service Bulletin 2/52, dated August 30, 1998, and deHavilland 
Beaver Service Bulletin TB/60, dated August 30, 1998. The NPRM also 
proposed to require repairing any crack found or replacing any cracked 
rear fuselage bulkhead. Accomplishment of the proposed repair or 
replacement as specified in the NPRM would be required in accordance 
with a repair or replacement scheme obtained from the manufacturer 
through the FAA.
    The NPRM was the result of mandatory continuing airworthiness 
information (MCAI) issued by the airworthiness authority for Canada.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposed rule or the FAA's determination of the cost to the public.

The FAA's Determination

    After careful review of all available information related to the 
subject presented above, the FAA has determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. The FAA has determined that these minor 
corrections will not change the meaning of the AD and will not add any 
additional burden upon the public than was already proposed.

Compliance Time of This AD

    The compliance time of this AD is presented in both calendar time 
and hours time-in-service (TIS). While cracks are generally a result of 
classic fatigue (i.e., aging and cyclic operation), the FAA believes 
that cracks could develop over time regardless of how often the 
airplane is operated. In order to assure that rear fuselage bulkhead 
cracking does not go undetected, a compliance time of specific hours 
TIS and calendar time (whichever occurs first) is utilized.

Cost Impact

    The FAA estimates that 350 airplanes in the U.S. registry will be 
affected by this AD, that it will take approximately 1 workhour per 
airplane to accomplish the initial inspection, and that the average 
labor rate is approximately $60 an hour. Based on these figures, the 
total cost impact of the initial inspection on U.S. operators is 
estimated to be $21,000, or $60 per airplane.
    These figures only take into the account the costs of the initial 
inspection and do not take into account the costs of the repetitive 
inspections or the cost of any repair or replacement necessary if any 
rear fuselage bulkhead is found cracked. The FAA has no way of 
determining the number of repetitive inspections each owner/operator 
will incur over the life of his/her affected airplane or the number of 
airplanes that will have a cracked rear fuselage bulkhead and need 
repair or replacement.

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 copy of the final evaluation prepared for this 
action is contained in the Rules Docket. A copy of it may be obtained 
by contacting 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 a new airworthiness directive 
(AD) to read as follows:

99-15-07  DeHavilland Inc.: Amendment 39-11226; Docket No. 99-CE-05-
AD.

    Applicability: Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. 
III airplanes, all serial numbers, 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 in the body of this AD, unless 
already accomplished.
    To detect and correct cracking of the rear fuselage bulkhead at 
Station 228, which could result in structural damage of the fuselage 
to the point of failure with consequent loss of airplane control, 
accomplish the following:
    (a) Within the next 400 hours time-in-service (TIS) after the 
effective date of this AD or within the next 12 calendar months 
after the effective date of this AD, whichever occurs first, and 
thereafter at intervals not to exceed 2,000 hours TIS or 5 years, 
whichever occurs first, inspect the rear fuselage bulkhead at 
Station 228 for cracks. Inspect in accordance with the 
Accomplishment Instructions section of whichever of the following 
service bulletins that is applicable:
    (1) For the Models DHC-2 Mk. I and DHC-2 Mk. II airplanes: 
deHavilland Beaver

[[Page 39003]]

Service Bulletin 2/52, dated August 30, 1998; or
    (2) For the Model DHC-2 Mk. III airplanes: deHavilland Beaver 
Service Bulletin TB/60, dated August 30, 1998.
    (b) If any crack(s) is/are found in the rear fuselage bulkhead 
at Station 228 during any inspection required by paragraph (a) of 
this AD, prior to further flight, accomplish the following:
    (1) Obtain a repair or replacement scheme from the manufacturer 
through the FAA, New York Aircraft Certification Office (ACO), 10 
Fifth Street, 3rd Floor, Valley Stream, New York 11581-1200; 
facsimile: (516) 568-2716.
    (2) Incorporate this repair or replacement scheme.
    (c) 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.
    (d) An alternative method of compliance or adjustment of the 
initial or repetitive compliance times that provides an equivalent 
level of safety may be approved by the Manager, New York ACO, 10 
Fifth Street, 3rd Floor, Valley Stream, New York 11581-1200. The 
request shall be forwarded through an appropriate FAA 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.

    (e) Questions or technical information related to deHavilland 
Beaver Service Bulletin TB/60, dated August 30, 1998, and 
deHavilland Beaver Service Bulletin 2/52, dated August 30, 1998, 
should be directed to Bombardier Inc., Bombardier Regional Aircraft 
Division, Garratt Boulevard, Downsview, Ontario, Canada M3K 1Y5; 
telephone: (416) 633-7310. This service information may be examined 
at the FAA, Central Region, Office of the Regional Counsel, Room 
1558, 601 E. 12th Street, Kansas City, Missouri 64106.
    (f) The inspections required by this AD shall be done in 
accordance with deHavilland Beaver Service Bulletin TB/60, dated 
August 30, 1998, or deHavilland Beaver Service Bulletin 2/52, dated 
August 30, 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, Garratt Boulevard, Downsview, 
Ontario, Canada M3K 1Y5. Copies may be inspected at the FAA, Central 
Region, Office of the Regional Counsel, Room 1558, 601 E. 12th 
Street, Kansas City, Missouri, 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 AD No. 
CF-98-38, dated October 15, 1998.

    (g) This amendment becomes effective on September 10, 1999.

    Issued in Kansas City, Missouri, on July 12, 1999.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 99-18197 Filed 7-20-99; 8:45 am]
BILLING CODE 4910-13-P