AD 2001-08-05

[Federal Register Volume 66, Number 78 (Monday, April 23, 2001)]
[Rules and Regulations]
[Pages 20377-20378]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-9666]



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Federal Register / Vol. 66, No. 78 / Monday, April 23, 2001 / Rules 
and Regulations

[[Page 20377]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-181-AD; Amendment 39-12182; AD 2001-08-05]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-7-100, -101, -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 Bombardier Model DHC-7-100, -101, -102, and -103 
series airplanes, that requires inspecting the endcaps of the main 
landing gear selector valve for leaks of hydraulic oil and, if leaks 
are detected, replacing the leaking endcaps or the entire selector 
valve. This amendment also requires eventual replacement or rework of 
certain selector valves, which would terminate the repetitive 
inspections. This amendment is prompted by a report of the collapse of 
the main landing gear due to an external leak of hydraulic oil in the 
landing gear selector valve, resulting from a fracture of the endcap. 
The actions specified by this AD are intended to prevent leaks of 
hydraulic oil from the main landing gear selector valve, which could 
result in the collapse of the main landing gear.

DATES: Effective May 29, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 29, 2001.

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 FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, 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: James E. Delisio, Aerospace Engineer, 
ANE-171, FAA, New York Aircraft Certification Office, 10 Fifth Street, 
Third Floor, Valley Stream, New York 11581; telephone (516) 256-7521; 
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-7-
100, -101, -102, and -103 series airplanes was published in the Federal 
Register on October 12, 2000 (65 FR 60595). That action proposed to 
require inspecting the endcaps of the main landing gear selector valve 
for leaks of hydraulic oil and, if leaks are detected, replacing the 
leaking endcaps or the entire selector valve. That action also proposed 
to require eventual replacement or rework of certain selector valves, 
which would terminate the repetitive inspections.

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.

Explanation of Change to Final Rule

    Since the issuance of the proposed rule, the FAA has received 
information from an operator indicating that replacement of the 
existing aluminum endcaps with stainless steel endcaps having part 
number (P/N) 52982, on a main landing gear selector valve having P/N 
57420-5, is the same terminating action as that specified in paragraph 
(c)(2) of the final rule. The FAA has determined that this is accurate 
information and has changed the final rule to specify that such 
replacement constitutes terminating action for the repetitive 
inspections required by paragraph (a) of the final rule. Paragraphs 
(b)(1) and (c)(2) of the final rule have been revised for 
clarification.

Conclusion

    After careful review of the available data, the FAA has determined 
that air safety and the public interest require the adoption of the 
rule with the changes described previously. The FAA has determined that 
these changes will neither increase the economic burden on any operator 
nor increase the scope of the AD.

Cost Impact

    The FAA estimates that 32 airplanes of U.S. registry will be 
affected by this AD, that it will require 1 work hour per airplane to 
accomplish the inspection, and that the average labor rate is $60 per 
work hour. Based on these figures, the cost impact of the inspection on 
U.S. operators is estimated to be $1,920, or $60 per airplane.
    The FAA also estimates that it will require 5 work hours per 
airplane to rework or replace the main landing gear selector valve and 
that the average labor rate is $60 per work hour. Based on these 
figures, the cost impact of the rework or replacement on U.S. operators 
is estimated to be $9,600 or $300 per airplane.
    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. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.
    Should an operator elect to replace the endcaps and perform the 
optional repetitive inspections prior to replacing the main landing 
gear selector valve, it would take approximately 1 work hour per 
airplane to conduct each inspection. Based on these figures, the cost 
impact of the optional repetitive inspections is estimated to be $60 
per inspection per airplane.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect on

[[Page 20378]]

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:

2001-08-05  Bombardier, Inc. (Formerly de Havilland, Inc.): 
Amendment 39-12182. Docket 2000-NM-181-AD.

    Applicability: Model DHC-7-100, -101, -102, and -103 series 
airplanes, serial numbers 003 through 113 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 
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 prevent the collapse of the main landing gear due to leaks of 
hydraulic oil from the main landing gear selector valve, accomplish 
the following:

Inspection

    (a) Within 100 flight cycles after the effective date of this 
AD, perform a general visual inspection of both endcaps of the main 
landing gear selector valve for the presence of hydraulic oil, in 
accordance with the Accomplishment Instructions of Bombardier Alert 
Service Bulletin A7-32-103, dated September 3, 1999. If no hydraulic 
oil is detected on either endcap, repeat the inspection at intervals 
not to exceed 400 flight hours until the requirements of paragraph 
(c) of this AD are accomplished.

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

Replacement or Modification

    (b) If any hydraulic oil is detected on either endcap: Prior to 
further flight, perform the actions specified in either paragraph 
(b)(1) or (b)(2) of this AD.
    (1) Replace the existing aluminum endcaps (on the selector 
valve), part number (P/N) 34629, with new stainless steel endcaps 
having P/N 52982, in accordance with the Accomplishment Instructions 
of Bombardier Alert Service Bulletin A7-32-103, dated September 3, 
1999. For main landing gear selector valves having P/N 57420-5, 
replacement of the endcaps terminates the repetitive inspection 
requirements of this AD.
    (2) Replace the main landing gear selector valve with a valve 
having P/N 57420-5A, in accordance with the Accomplishment 
Instructions of Bombardier Alert Service Bulletin A7-32-103, dated 
September 3, 1999.

    Note 3: Use care when removing the endcaps, so that the internal 
components do not fall on the ground and get damaged.

    (c) Within 12 months after the effective date of this AD: 
Perform the actions specified in either paragraph (c)(1) or (c)(2) 
of this AD, in accordance with the Accomplishment Instructions of 
Bombardier Alert Service Bulletin A7-32-103, dated September 3, 
1999. Accomplishment of either paragraph (c)(1) or (c)(2) terminates 
the repetitive inspection requirements of this AD.
    (1) If a main landing gear selector valve having P/N 57420-1 or 
57420-3 is installed, remove it and replace it with a valve having 
P/N 57420-5A.
    (2) If a main landing gear selector valve having P/N 57420-5 is 
installed, remove it and replace it with a valve having P/N 57420-5A 
or modify the valve to the P/N 57420-5A configuration (Modification 
7/2742). For main landing gear selector valves having P/N 57420-5, 
replacement of the endcaps, as specified in paragraph (b)(1) of this 
AD, terminates the repetitive inspection requirements 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 Aircraft Certification 
Office (ACO), FAA. 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 4: 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 
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

    (f) The actions shall be done in accordance with Bombardier 
Alert Service Bulletin A7-32-103, dated September 3, 1999. 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, 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 5: The subject of this AD is addressed in Canadian 
airworthiness directive CF-99-31, dated December 21, 1999.

Effective Date

    (g) This amendment becomes effective on May 29, 2001.

    Issued in Renton, Washington, on April 12, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-9666 Filed 4-20-01; 8:45 am]
BILLING CODE 4910-13-U