AD 2000-02-07

[Federal Register Volume 65, Number 18 (Thursday, January 27, 2000)]
[Rules and Regulations]
[Pages 4354-4356]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-1767]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-107-AD; Amendment 39-11526; AD 2000-02-07]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-7-100 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 all Bombardier Model DHC-7-100 series airplanes, that 
requires repetitive high frequency eddy current inspections to detect 
cracks on the locking pin fittings of the baggage door and locking pin 
housings of the fuselage; repetitive detailed visual inspections to 
detect cracks of the inner door structure on all four door locking 
attachment fittings; and corrective actions, if necessary. In lieu of 
accomplishing the corrective actions, this amendment also provides a 
temporary option, for certain cases, for revising the Airplane Flight 
Manual (AFM), and installing a placard. 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 detect and correct fatigue cracking of the baggage door 
fittings and the support structure, which could result in structural 
failure, and consequent rapid decompression of the airplane during 
flight.

DATES:  Effective March 2, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 2, 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 all Bombardier Model DHC-7-100 
series airplanes was published in the Federal Register on November 22, 
1999 (64 FR 63760). That action proposed to require repetitive high 
frequency eddy current inspections to detect cracks on the locking pin 
fittings of the baggage door and locking pin housings of the fuselage; 
repetitive detailed visual inspections to detect cracks of the inner 
door structure on all four door locking attachment fittings; and 
corrective actions, if necessary. In lieu of accomplishing the 
corrective actions, that action also proposed to provide a temporary 
option, for certain cases, for revising the Airplane Flight Manual 
(AFM), and installing a placard.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The commenter supports the proposed rule.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Interim Action

    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.

Cost Impact

    The FAA estimates that 32 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 3 work hours per 
airplane to accomplish the required inspections, 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 $5,760, or $180 
per airplane, per inspection cycle.
    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

[[Page 4355]]

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:

2000-02-07  Bombardier, Inc. (Formerly de Havilland, Inc.): 
Amendment 39-11526. Docket 99-NM-107-AD.
    Applicability: All Model DHC-7-100 series airplanes, 
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 detect and correct fatigue cracking in the baggage door 
fittings and the support structure, which could result in structural 
failure, and consequent rapid decompression of the airplane during 
flight, accomplish the following:

Repetitive Inspections

    (a) At the latest of the times specified in paragraphs (a)(1) 
and (a)(2) of this AD, perform a high frequency eddy current 
inspection to detect fatigue cracks of the locking pin fittings of 
the baggage door and locking pin housings of the fuselage; and a 
detailed visual inspection to detect fatigue cracks of the inner 
door structure on all four locking attachment fittings of the 
baggage door; in accordance with de Havilland Temporary Revision 
(TR) 5-100, dated December 23, 1998, for Supplementary Inspection 
Task 52-1 to the de Havilland Dash 7 Maintenance Manual PSM 1-7-2. 
Thereafter, repeat the inspections at intervals not to exceed 1,000 
flight cycles.
    (1) Inspect prior to the accumulation of 12,000 total flight 
cycles.
    (2) Inspect within 600 flight cycles or 3 months after the 
effective date of this AD, whichever occurs later.


    Note 2:  For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

Corrective Actions

    (b) If any crack is detected during any inspection required by 
paragraph (a) of this AD, prior to further flight, accomplish the 
requirements of paragraphs (b)(1) and (b)(2) of this AD, as 
applicable, except as provided in paragraph (c) of this AD. For 
operators that elect to accomplish the actions specified in 
paragraph (c) of this AD: After accomplishment of the replacement 
required by paragraph (b)(1) or (b)(2) of this AD, the AFM revision 
and placard required by paragraph (c) of this AD may be removed.
    (1) If a crack is detected in a baggage door locking pin fitting 
or fuselage locking pin housing: Replace the fitting or housing with 
a new fitting or housing, as applicable, in accordance with de 
Havilland Dash 7 Maintenance Manual PSM 1-7-2.
    (2) If a crack is detected in the inner baggage door structure 
at the locking attachment fittings: Replace the structure with a new 
support structure in accordance with de Havilland Dash 7 Maintenance 
Manual PSM 1-7-2, or repair in accordance with a method approved by 
the Manager, New York Aircraft Certification Office (ACO), FAA, 
Engine and Propeller Directorate, or the Transport Canada Civil 
Aviation (or its delegated agent). 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.
    (c) For airplanes on which only one baggage door stop fitting or 
its support structure is found cracked at one location, and on which 
the pressurization system ``Dump'' function is operational: Prior to 
further flight, accomplish the requirements of paragraphs (c)(1) and 
(c)(2) of this AD. Within 1,000 flight cycles after accomplishment 
of the requirements of paragraphs (c)(1) and (c)(2) of this AD, 
accomplish the requirements of paragraph (b)(1) or (b)(2) of this 
AD, as applicable.
    (1) Revise the Limitations Section of the FAA-approved DHC-7 
Airplane Flight Manual (AFM), PSM 1-71A-1A, to include the following 
statement. This AFM revision may be accomplished by inserting a copy 
of this AD into the AFM.
    ``Flight is restricted to unpressurized flight below 10,000 feet 
mean sea level (MSL). The airplane must be operated in accordance 
with DHC-7 AFM, PSM 1-71A-1A, Supplement 20.''
    (2) Install a placard on the cabin pressure control panel or in 
a prominent location that states the following:
    ``DO NOT PRESSURIZE THE AIRCRAFT UNPRESSURIZED FLIGHT PERMITTED 
ONLY IN ACCORDANCE WITH DHC-7 AFM PSM 1-71A-1A, SUPPLEMENT 20 FLIGHT 
ALTITUDE LIMITED TO 10,000 FEET MSL OR LESS.''

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 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 3:  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 
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.

Incorporation by Reference

    (f) The inspections shall be done in accordance with de 
Havilland Temporary Revision 5-100, dated December 23, 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

[[Page 4356]]

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 4:  The subject of this AD is addressed in Canadian 
airworthiness directive CF-99-03, dated February 22, 1999.

    (g) This amendment becomes effective on March 2, 2000.

    Issued in Renton, Washington, on January 20, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 00-1767 Filed 1-26-00; 8:45 am]
BILLING CODE 4910 -13-P