[Federal Register Volume 69, Number 91 (Tuesday, May 11, 2004)]
[Rules and Regulations]
[Pages 26025-26027]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-10244]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-153-AD; Amendment 39-13612; AD 2000-02-07 R1]
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 revises an existing airworthiness directive 
(AD), applicable to all Bombardier Model DHC-7-100 series airplanes, 
that currently 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 
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 amendment also 
provides a temporary option, for certain cases, for revising the 
Airplane Flight Manual and installing a placard. That AD was prompted 
by issuance of mandatory continuing airworthiness information by a 
foreign civil airworthiness authority. The actions specified by that 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. This amendment extends the compliance time of the repetitive 
inspections based on test evidence and is intended to address the 
identified unsafe condition.

DATES: Effective June 15, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 15, 2004.

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, New York Aircraft Certification 
Office, 1600 Stewart Avenue, suite 410, Westbury, New York; or at the 
National Archives and Records Administration (NARA). For information on 
the availability of this material at NARA, call 202-741-6030, or go to 
http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: David Lawson, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New 
York 11590; telephone (516) 228-7327; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by revising AD 2000-02-07, 
amendment 39-11526 (65 FR 4354, January 27, 2000), which is applicable 
to all Bombardier Model DHC-7-100 series airplanes, was published in 
the Federal Register on January 29, 2004 (69 FR 4257). The 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 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 amendment also provides a 
temporary option, for certain cases, for revising the Airplane Flight 
Manual (AFM), and installing a placard. That action was prompted by 
issuance of mandatory continuing airworthiness information by a foreign 
civil airworthiness authority. The actions specified by that 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.

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.

Change to Final Rule

    We have changed paragraphs (b)(1) and (b)(2) of this final rule to 
specify that the actions shall be done 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). In addition, the de Havilland Dash 7 
Maintenance Manual PSM 1-7-2 is listed as one approved method of 
compliance for accomplishment of the actions.

Conclusion

    After careful review of the available data, we have determined that 
air safety and the public interest require the adoption of the rule 
with the change described previously. This change will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Changes to 14 CFR Part 39/Effect on the AD

    On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR 
47997, July 22, 2002), which governs our

[[Page 26026]]

airworthiness directives system. The regulation now includes material 
that relates to altered products, special flight permits, and 
alternative methods of compliance (AMOCs). However, for clarity and 
consistency in this final rule, we have retained the language of the 
NPRM regarding that material.

Cost Impact

    The changes in this action add no additional economic burden. The 
current costs for this AD are repeated for the convenience of affected 
operators, as follows:
    We estimate that 32 airplanes of U.S. registry will be affected by 
this AD, that it will take about 3 work hours per airplane to 
accomplish the inspections, and that the average labor rate is $65 per 
work hour. Based on these figures, the cost impact of the AD on U.S. 
operators is estimated to be $6,240, or $195 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 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.

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

0
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

0
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]

0
2. Section 39.13 is amended by removing amendment 39-11526 (65 FR 4354, 
January 27, 2000), and by adding a new airworthiness directive (AD), 
amendment 39-13612, to read as follows:

AD 2000-02-07 R1 Bombardier, Inc. (Formerly de Havilland, Inc.): 
Amendment 39-13612. Docket 2003-NM-153-AD. Revises AD 2000-02-07, 
Amendment 39-11526.

    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 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) 5-101, 
dated August 17, 2001, 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 10,000 flight cycles.
    (1) Inspect prior to the accumulation of 12,000 total flight 
cycles.
    (2) Inspect within 600 flight cycles or 3 months after March 2, 
2000 (the effective date of AD 2000-02-07, amendment 39-11526), 
whichever occurs later.

    Note 2: For the purposes of this AD, a detailed 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 Airplane 
Flight Manual (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 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). The de Havilland 
Dash 7 Maintenance Manual PSM 1-7-2 is one approved method.
    (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 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. The de Havilland Dash 7 Maintenance Manual PSM 1-7-2 is one 
approved method.
    (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 DHC-7 AFM, PSM 1-71A-
1A, to include the

[[Page 26027]]

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 
Sec. Sec.  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) Unless otherwise specified in this AD, the actions shall be 
done in accordance with de Havilland Temporary Revision 5-101, dated 
August 17, 2001, for Supplementary Inspection Task 52-1 to the de 
Havilland Dash 7 Maintenance Manual PSM 1-7-2. 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, 1600 Stewart Avenue, suite 410, 
Westbury, New York; or at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Note 4: The subject of this AD is addressed in Canadian 
airworthiness directive CF-99-03R1, dated August 22, 2001.

Effective Date

    (g) This amendment becomes effective on June 15, 2004.

    Issued in Renton, Washington, on April 22, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-10244 Filed 5-10-04; 8:45 am]
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