[Federal Register Volume 63, Number 237 (Thursday, December 10, 1998)]
[Rules and Regulations]
[Pages 68169-68171]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-32622]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-237-AD; Amendment 39-10935; AD 98-25-09]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-7 and DHC-8 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 and DHC-8 series 
airplanes, that requires a one-time visual inspection to determine the 
serial number of the brake shuttle valves of the main landing gear 
(MLG); and replacement of the filter fittings with new filter fittings, 
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 ensure that 
proper filter fittings are installed. Installation of improper filter 
fittings could result in failure of the brake shuttle valves, and 
consequent loss of brake effectiveness, which could reduce 
controllability of the airplane during taxi, takeoff, and landing roll.

DATES: Effective January 14, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 14, 1999.

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

[[Page 68170]]

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: Anthony E. Gallo, Aerospace Engineer, 
Systems and Flight Test Branch, ANE-172, FAA, Engine and Propeller 
Directorate, New York Aircraft Certification Office, 10 Fifth Street, 
Third Floor, Valley Stream, New York 11581; telephone (516) 256-7510; 
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 and 
DHC-8 series airplanes was published in the Federal Register on October 
2, 1998 (63 FR 52994). That action proposed to require a one-time 
visual inspection to determine the serial number of the brake shuttle 
valves of the main landing gear (MLG); and replacement of the filter 
fittings with new filter fittings, 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 260 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 inspection, and that the average 
labor rate is $60 per work hour. Based on these figures, the cost 
impact of the AD on U.S. operators is estimated to be $15,600, 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 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:

98-25-09 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 
39-10935. Docket 98-NM-237-AD.

Applicability: Model DHC-7-1, -100, -101, -102, and -103 series 
airplanes, having serial numbers (S/N) 003 through 113 inclusive; 
and Model DHC-8-100, -200, and -300 series airplanes, having S/N's 
003 through 498 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 (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 failure of the brake shuttle valves, and consequent 
loss of the brake effectiveness, due to installation of improper 
filter fittings, which could reduce controllability of the airplane 
during taxi, takeoff, and landing roll, accomplish the following:
    (a) Within 3 months after the effective date of this AD, perform 
a one-time visual inspection to determine the serial numbers of the 
brake shuttle valves of the main landing gear (MLG), in accordance 
with Bombardier Alert Service Bulletin S.B. A7-32-102, Revision `A,' 
dated November 26, 1997 (for Model DHC-7 series airplanes), or S.B. 
A8-32-139, Revision `A,' dated December 19, 1997 (for Model DHC-8 
series airplanes), as applicable. If any brake shuttle valve having 
S/N 2162A through 2244A inclusive is installed, prior to further 
flight, replace the filter fittings with new filter fittings, in 
accordance with the applicable alert service bulletin.
    (b) As of the effective date of this AD, no person shall install 
a brake shuttle valve having part number 5084-1 on any airplane, 
unless it has been inspected and any defective filter fitting 
replaced, in accordance with the requirements of this AD.
    (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.

    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.

    (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 inspection and replacement shall be done in accordance 
with Bombardier Alert Service Bulletin S.B. A7-32-102, Revision `A,' 
dated November 26, 1997, or Bombardier Alert Service Bulletin S.B. 
A8-32-139, Revision `A,' dated December 19, 1997, as applicable. 
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.

[[Page 68171]]

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-98-05, dated March 2, 1998.

    (f) This amendment becomes effective on January 14, 1999.

    Issued in Renton, Washington, on December 2, 1998.
John W. McGraw,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-32622 Filed 12-9-98; 8:45 am]
BILLING CODE 4910-13-P