[Federal Register Volume 65, Number 228 (Monday, November 27, 2000)]
[Rules and Regulations]
[Pages 70648-70650]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-29375]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-76-AD; Amendment 39-11992; AD 2000-23-19]
RIN 2120-AA64


Airworthiness Directives; Saab Model SAAB SF340A and SAAB 340B 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series 
airplanes, that currently requires inspections to detect damage or 
cracking of the forward and aft attachment lugs of the flap fittings at 
wing station (WS) 123.38; an inspection to verify that the sizes of the 
holes of the flap fittings are within specified limits and to ensure 
that the swaged bushings are not loose; and modification of the flap 
fittings. This amendment requires repetitive accomplishment of the 
inspections using improved inspection methods; a one-time visual and 
repetitive general visual and detailed visual inspections; new 
repetitive non-destructive test (NDT) inspections; and corrective and 
follow-on actions, as necessary. This amendment also provides for 
terminating action for all repetitive inspections and revises the 
applicability of the existing AD. The actions specified by this AD are 
intended to prevent high bearing stress on the bushings of the flap 
fittings, which could result in wear on the bushings, cracking of the 
flap fittings, and breakage of the lugs; these conditions could result 
in jamming of the flaps and consequent reduced controllability of the 
airplane.

DATES: Effective January 2, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 2, 2001.

ADDRESSES: The service information referenced in this AD may be 
obtained from Saab Aircraft AB, SAAB Aircraft Product Support, S-
581.88, Linkoping, Sweden. 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 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, 
International Branch, ANM-116, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 96-25-06 R1, 
amendment 39-9891 (62 FR 3209, January 22, 1997), which is applicable 
to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, was 
published in the Federal Register on July 31, 2000 (65 FR 46667). The 
action proposed to continue to require inspections to detect damage or 
cracking of the forward and aft attachment lugs of the flap fittings at 
wing station (WS) 123.38; an inspection to verify that the sizes of the 
holes of the flap fittings are within specified limits and to ensure 
that the swaged bushings are not loose; and modification of the flap 
fittings. The action also proposed to require repetitive accomplishment 
of the inspections using improved inspection methods; a one-time visual 
and repetitive general visual and detailed visual inspections; new 
repetitive non-destructive test (NDT) inspections; and corrective and 
follow-on actions, as necessary. Additionally, the action also proposed 
to provide for terminating action for all repetitive inspections and to 
revise the applicability of the existing AD.

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 303 airplanes of U.S. registry will be 
affected by this AD.
    It will take approximately 1 work hour per airplane to accomplish 
the required repetitive general visual inspections, at an average labor 
rate of $60 per work hour.
    Based on these figures, the cost impact of the required general 
visual inspections on U.S. operators is estimated to be $18,180, or $60 
per airplane, per inspection cycle.
    It will take approximately 1 work hour per airplane to accomplish 
the required one-time general visual inspection, at an average labor 
rate of $60 per work hour. Based on these figures, the cost impact of 
the required general visual inspection on U.S. operators is estimated 
to be $18,180, or $60 per airplane.
    It will take approximately 1 work hour per airplane to accomplish 
the required repetitive detailed visual inspections, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the required detailed visual inspections on U.S.

[[Page 70649]]

operators is estimated to be $18,180, or $60 per airplane, per 
inspection cycle.
    It will take approximately 2 work hours per airplane to accomplish 
the required repetitive NDT inspections, at an average labor rate of 
$60 per work hour. Based on these figures, the cost impact of the 
required NDT inspections on U.S. operators is estimated to be $36,360, 
or $120 per airplane, per inspection cycle.
    Should an operator be required or elect to accomplish the 
terminating modification, it will take approximately 92 work hours per 
airplane (46 work hours per flap), at an average labor rate of $60 per 
hour. Required parts will cost $7,362 per airplane ($3,681 per flap). 
Based on these figures, the cost impact of the terminating modification 
on U.S. operators is estimated to be $12,882 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.

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 removing amendment 39-9891 (62 FR 
3209, January 22, 1997), and by adding a new airworthiness directive 
(AD), amendment 39-11992, to read as follows:

2000-23-19 SAAB Aircraft AB: Amendment 39-11992. Docket 2000-NM-76-
AD. Supersedes AD 96-25-06 R1, Amendment 39-9891.

    Applicability: Model SAAB SF340A series airplanes, 
manufacturer's serial numbers -004 through -159 inclusive; and SAAB 
340B series airplanes, manufacturer's serial numbers -160 through -
459 inclusive; certificated in any category; on which any flap 
assembly having part number (P/N) 7257800-501 through 508 inclusive, 
or 7257800-851 through 7257800-856 inclusive, is installed.

    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 high bearing stress on the bushings in the flap 
fittings, which could result in jamming of the flaps and consequent 
reduced controllability of the airplane, accomplish the following:

Visual Inspection for Serial Numbers

    (a) Within 800 flight hours after the effective date of this AD, 
perform a one-time visual inspection of the flap assemblies of the 
flap fittings at wing station (WS) 123.38 to determine the flap 
assembly serial numbers, in accordance with Saab Service Bulletin 
340-57-035, dated January 18, 2000.
    (1) If none of the serial numbers of the flap assemblies are 
listed in the service bulletin, no further action is required by 
this paragraph.
    (2) If the serial number of any flap assembly is listed in the 
service bulletin, prior to further flight, accomplish the 
requirements of paragraph (a)(2)(i) and, at the time specified, 
accomplish the requirements of paragraph (a)(2)(ii) of this AD.

General Visual Inspection, Non-Destructive Test (NDT) Inspection, and 
Replacement of Bolts and Bushings

    (i) Perform a general visual inspection of the affected flap 
fittings at WS 123.38 to detect cracking, in accordance with the 
service bulletin. If no cracking is detected, repeat the visual 
inspection thereafter at intervals not to exceed 800 flight hours, 
until the requirements of paragraph (a)(2)(ii) of this AD are 
accomplished. If any cracking is detected, prior to further flight, 
accomplish the terminating action specified by paragraph (c) of this 
AD.
    (ii) Within 4,800 flight hours after the effective date of this 
AD, perform a one-time detailed visual inspection of the flap 
fittings to determine the size of the inboard and outboard holes 
(swaged bushing) and to detect loose swaged bushings; and perform an 
NDT inspection of the aft attachment lugs of the flap assemblies at 
WS 123.38 to detect cracking, in accordance with the service 
bulletin. Accomplishment of the NDT inspection terminates the 
general visual inspection required by paragraph (a)(2)(i) of this 
AD.

    Note 2: For the purpose 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.''


    Note 3: 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 mirrors, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

    (A) If all the hole sizes are within the limits specified by the 
service bulletin, no loose swaged bushings are found, and no 
cracking of the aft attachment lugs is detected: Prior to further 
flight, install new fasteners that attach to the flap hinges (nuts, 
bolts, bushing, and washers), in accordance with the service 
bulletin.
    (B) If any hole size is outside the limits specified by the 
service bulletin, or any loose swaged bushing is found, or any 
cracking is

[[Page 70650]]

detected on the aft attachment lugs: Prior to further flight, 
accomplish the terminating action specified in paragraph (c) of this 
AD.

Visual Inspection for Modification Status

    (b) Within 800 flight hours after the effective date of this AD, 
perform a one-time visual inspection of the aft attachment lugs 
(flap assemblies) of the flap fittings at wing station (WS) 123.38 
to determine the flap assembly modification status, in accordance 
with Saab Service Bulletin 340-57-037, dated January 18, 2000.
    (1) If the modification status is such that all flap assemblies 
installed have thicker lugs, as specified by Figure 1 of the service 
bulletin, no further action is required by this paragraph.
    (2) If the modification status is such that any flap assembly 
installed has a thinner lug, as specified by Figure 1 of the service 
bulletin, prior to further flight, accomplish the requirements of 
paragraph (b)(2)(i) and, at the time specified, accomplish the 
requirements of paragraph (b)(2)(ii) of this AD.

Visual Inspection and NDT Inspection

    (i) Perform a general visual inspection of the aft attachment 
lugs of the flap fittings at WS 123.38 to detect cracking or damage, 
in accordance with the service bulletin. If no cracking or damage is 
detected during the visual inspection, repeat the inspection 
thereafter at intervals not to exceed 800 flight hours, until the 
requirements of paragraph (b)(2)(ii) of this AD are accomplished. If 
any cracking or damage is detected during any general visual 
inspection required by this paragraph, prior to further flight, 
accomplish the terminating action specified by paragraph (c) of this 
AD.
    (ii) Within 6,000 flight cycles after the effective date of this 
AD, perform an NDT inspection of the aft attachment lug of the flap 
fittings at WS 123.38 to detect cracking, in accordance with the 
service bulletin. Accomplishment of the NDT inspection terminates 
the repetitive visual inspections required by paragraph (b)(2)(i) of 
this AD. If no cracking is detected, repeat the NDT inspection 
thereafter at intervals not to exceed 6,000 flight cycles, until the 
actions specified by paragraph (c) are accomplished. If any cracking 
is detected during any NDT inspection required by this paragraph, 
prior to further flight, accomplish the terminating action specified 
by paragraph (c) of this AD.

Terminating Action

    (c) Replacement of all flap fittings at WS 123.38 with new, 
improved flap fittings in accordance with Saab Service Bulletin 340-
57-038, dated January 18, 2000, terminates all inspections required 
by 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, International Branch, ANM-116, FAA, 
Transport Airplane Directorate. Operators shall submit their 
requests through an appropriate FAA Principal Maintenance Inspector, 
who may add comments and then send it to the Manager, International 
Branch, ANM-116.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

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 actions shall be done in accordance with Saab Service 
Bulletin 340-57-035, dated January 18, 2000; Saab Service Bulletin 
340-57-037, dated January 18, 2000; and Saab Service Bulletin 340-
57-038, dated January 18, 2000; 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 Saab Aircraft AB, SAAB Aircraft Product Support, S-
581.88, Linkoping, Sweden. Copies may be inspected at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; 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 Swedish 
airworthiness directives No. 1-152 and No. 1-153, each dated January 
19, 2000.

Effective Date

    (g) This amendment becomes effective on January 2, 2001.


    Issued in Renton, Washington, on November 9, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-29375 Filed 11-24-00; 8:45 am]
BILLING CODE 4910-13-U