Airworthiness Directives; Saab Model SAAB SF340A and SAAB 340B Series Airplanes, 7851-7853 [05-2832]

Download as PDF Federal Register / Vol. 70, No. 31 / Wednesday, February 16, 2005 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–19447; Directorate Identifier 2004–NM–97–AD; Amendment 39– 13976; AD 2005–04–04] RIN 2120–AA64 Airworthiness Directives; Saab Model SAAB SF340A and SAAB 340B Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all Saab Model SAAB SF340A and SAAB 340B series airplanes. This AD requires a onetime inspection to determine the part and serial numbers of certain engine vibration isolators (mounts) and the cure dates of certain molded assemblies incorporated in those engine mounts; and related corrective actions if necessary. This AD is prompted by a report that disbonding of the elastomer from the inner metal core and shim of certain engine vibration mounts has occurred within a few hundred hours of operation, causing heavy chafing of the engine support system and chafing of the fire sensor loop. We are issuing this AD to prevent reduced integrity of the fire-shielding capacity of the nacelle structure and a possible fire detector fault. This AD becomes effective March 23, 2005. The incorporation by reference of a certain publication listed in the AD is approved by the Director of the Federal Register as of March 23, 2005. ADDRESSES: For service information identified in this AD, contact Saab Aircraft AB, SAAB Aircraft Product Support, S–581.88, Linkping, Sweden. You can examine this information 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: https://www.archives.gov/ federal_register/ code_of_federal_regulations/ ibr_locations.html. Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can examine the AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The DATES: VerDate jul<14>2003 10:50 Feb 15, 2005 Jkt 205001 Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Washington, DC. This docket number is FAA–2004–19447; the directorate identifier for this docket is 2004–NM– 97–AD. FOR FURTHER INFORMATION CONTACT: Mike Borfitz, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2677; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39 with an AD for all Saab Model SAAB SF340A and SAAB 340B series airplanes. That action, published in the Federal Register on October 27, 2004 (69 FR 62625), proposed to require a one-time inspection to determine the part and serial numbers of certain engine vibration isolators (mounts) and the cure dates of certain molded assemblies incorporated in those engine mounts; and related corrective actions if necessary. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment that has been submitted on the proposed AD. Request To Withdraw Proposed AD The commenter requests that the proposed AD be withdrawn. The commenter states that delamination of a bonded canister (molded assembly) is readily apparent and would have been detected during the scheduled inspections recommended in the Saab maintenance program. The commenter also mentions that the molded assemblies have a life limit of 5,000 flight hours, at which point those assemblies are removed from the airplane. The commenter notes that by the time the proposed AD is issued, almost three years would have passed since the affected molded assemblies were put into service. The commenter remarks that it is unlikely that any affected molded assembly remaining in the field would not have already been identified and removed from service during the regularly scheduled maintenance inspection program. The commenter states that, for the reasons mentioned above, the FAA needs to consider the timing of the proposed AD. The commenter suggests that, at this late date, the unsafe condition regarding the removal of molded assemblies subject to PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 7851 delamination would have resolved itself. We do not agree with the commenter’s request to withdraw this AD. The procedures specified in a service bulletin are not mandatory. Therefore, we must issue an AD to ensure that the identified unsafe condition is properly addressed. Even if the current U.S.registered fleet is in compliance with the requirements of this AD, the issuance of the rule is still necessary to ensure that any affected airplane that is imported and placed on the U.S. register in the future will be required to be in compliance as well. We also want to ensure that, if the subject molded assemblies are currently in an operator’s spare parts inventory, the actions required by this AD are performed. In addition, as provided by paragraph (e) of this AD, operators who have already done all of the actions required by this AD are already in compliance with this AD, and no further action is required by them. Furthermore, the requirements of this AD include a general visual inspection for chafing of the nacelle structure and fire sensor loop. This inspection is necessary because chafing of the nacelle structure and fire sensor loop is part of the unsafe condition addressed by this AD. We must ensure that operators did this inspection and did not just replace the engine mounts. Also, the airworthiness authority for the state of design issued an airworthiness directive mandating the same actions required by this AD. No change has been made to this AD regarding this issue. Changes to This AD We have added a new paragraph (g), Parts Installation, in this AD to clarify that, prior to the installation of an engine vibration mount on an airplane, the part and serial number of the engine vibration mount, and the cure date of the molded assembly incorporated in the engine mount must be determined, and any applicable corrective action accomplished before further flight, in accordance with the requirements of paragraph (f) of this AD. Although this was our intent in the proposed AD, the Parts Installation paragraph was inadvertently omitted from the proposed AD. The subsequent paragraphs in this AD have been reidentified accordingly. Also, for clarification purposes, certain terminology in the proposed AD has been changed in this AD. The phrase ‘‘molded assembly engine mounts (isolators)’’ has been changed to ‘‘engine vibration isolators (mounts).’’ The term ‘‘bonded canister assemblies’’ E:\FR\FM\16FER1.SGM 16FER1 7852 Federal Register / Vol. 70, No. 31 / Wednesday, February 16, 2005 / Rules and Regulations has been changed to ‘‘molded assemblies.’’ Conclusion We have carefully reviewed the available data, including the comment that has been submitted, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance This AD affects about 170 airplanes of U.S. registry. The required actions will take about 2 work hours per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of this AD for U.S. operators is $22,100 or $130 per airplane. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD 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. For the reasons discussed above, I certify that this AD: (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, VerDate jul<14>2003 10:50 Feb 15, 2005 Jkt 205001 on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD. See the ADDRESSES section for a location to examine the regulatory evaluation. assemblies incorporated in those engine mounts; and a general visual inspection for chafing of the nacelle structure and fire sensor loop; and related corrective actions, as applicable; in accordance with the Accomplishment Instructions of Saab Service Bulletin 340–71–059, dated May 16, 2003. Corrective actions must be accomplished prior to further flight. List of Subjects in 14 CFR Part 39 Note 1: Saab Service Bulletin 340–71–059 refers to Barry Controls Service Letter 93948– 71–05, dated April 30, 2003, as an additional source of service information. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): I 2005–04–04 SAAB Aircraft AB: Amendment 39–13976. Docket No. FAA–2004–19447; Directorate Identifier 2004–NM–97–AD. Effective Date (a) This AD becomes effective March 23, 2005. Affected ADs (b) None. Applicability (c) This AD applies to all Model SAAB SF340A and SAAB 340B series airplanes, certificated in any category. Unsafe Condition (d) This AD was prompted by a report that disbonding of the elastomer from the inner metal core and shim of certain engine vibration isolators (mounts) has occurred within a few hundred hours of operation, causing heavy chafing of the engine support system and chafing of the fire sensor loop. We are issuing this AD to prevent reduced integrity of the fire-shielding capacity of the engine nacelle structure and a possible fire detector fault. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspection (f) Within 500 flight hours after the effective date of this AD, perform a one-time inspection to determine the part and serial numbers of certain engine vibration mounts, and the cure dates of certain molded PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 Note 2: For the purposes of this AD, a general visual inspection is ‘‘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 from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normal available lighting conditions such as daylight, hangar lighting, flashlight or droplight 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.’’ Parts Installation (g) As of the effective date of this AD, no person may install on any airplane an engine vibration mount unless the part and serial number of the engine vibration mount, and the cure date of the molded assembly incorporated in the engine mount, have been determined and any applicable corrective action accomplished before further flight, in accordance with the requirements of paragraph (f) of this AD. Alternative Methods of Compliance (AMOCs) (h) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Related Information (i) Swedish airworthiness directive SAD 1– 192, dated May 16, 2003, also addresses the subject of this AD. Material Incorporated by Reference (j) You must use Saab Service Bulletin 340–71–059, dated May 16, 2003, including Attachment 1, dated April 30, 2003; to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For copies of the service information, contact Saab Aircraft AB, SAAB Aircraft ¨ Product Support, S–581.88, Linkoping, Sweden. For information on the availability of this material at the National Archives and Records Administration (NARA), call (202) 741–6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. You may view the AD docket at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., E:\FR\FM\16FER1.SGM 16FER1 Federal Register / Vol. 70, No. 31 / Wednesday, February 16, 2005 / Rules and Regulations room PL–401, Nassif Building, Washington, DC. Issued in Renton, Washington, on January 31, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–2832 Filed 2–15–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF STATE 22 CFR Part 41 [Public Notice 4992] RIN 1400–AC03 Documentation of Nonimmigrants Under the Immigration and Nationality Act, as Amended—Student and Exchange Visitor Information System (SEVIS) State Department. Final rule. AGENCY: ACTION: SUMMARY: This rule makes final the interim rule amending the Department’s regulations pertaining to foreign students and exchange visitors who enter the United States in F, M, or J nonimmigrant visa categories. The new regulations will establish the verification and reporting procedures required by the Department of Homeland Security (DHS) foreign student monitoring system known as Student and Exchange Visitor Information System (SEVIS). As SEVIS was fully implemented on February 15, 2003, the Department’s transitional foreign student database known as the Interim Student and Exchange Authentication System (ISEAS) is no longer available to the educational and exchange visitor communities. However, it remains available to consular sections in the field as a means of electronically verifying student and exchange visitor documentation issued prior to February 15, 2003. EFFECTIVE DATES: The interim rule became effective on May 23, 2003. This final rule takes effect on the date of publication in the Federal Register. ADDRESSES: You may view this final rule online at https://www.regulations.gov/. FOR FURTHER INFORMATION CONTACT: Jill Nebel, Legislation and Regulations Division, Visa Services, Department of State, Washington, DC 20520–0106, 202–663–1260 or e-mail nebelj@state.gov On May 23, 2003, the Department published an interim rule (68 FR 28129; Public Notice 4368) detailing the implementation of SUPPLEMENTARY INFORMATION: VerDate jul<14>2003 10:50 Feb 15, 2005 Jkt 205001 the SEVIS monitoring system. The Department published this interim rule with a request for comments. There were no comments received and the Department is now making final the interim rule. How Is the Department Amending Its Regulations? The Department is amending its regulations at 22 CFR 41.61 and 41.62 regarding students and exchange visitors by adding the requirement that authorized consular officials verify the provenance of SEVIS-generated forms I– 20 or DS–2019 against SEVIS data in the Consular Consolidated Database CCD. It is also amending its regulations by adding the requirement that authorized consular officials verify the payment of any applicable SEVIS fee, and to make Border Commuter Students (F–3 and M– 3) subject to SEVIS requirements. No F– 1, F–2, F–3, M–1, M–2, M–3, J–1 or J– 2 visas may be issued unless an authorized consular official has verified the provenance of the student or exchange visitor acceptance documentation against SEVIS data in the CCD, or via direct access to SEVIS. Regulatory Findings Administrative Procedure Act The Department is publishing this rule as a final rule, after a 60-day provision for post-promulgation public comments and review, based on the ‘‘good cause’’ exceptions set forth at 5 U.S.C. 553(b)(3)(B) and 553(d)(3). Regulatory Flexibility Act The Department of State, in accordance with the Regulatory Flexibility Act (5 U.S.C. 605(b)), has reviewed this regulation and, by approving it, certifies that this rule will not have a significant economic impact on a substantial number of small entities. The Small Business Regulatory Enforcement Fairness Act of 1996 This rule is not a major rule as defined by section 804 of the Small Business Regulatory Enforcement Act of 1996. This rule will not result in an annual effect on the economy of $100 million or more; a major increase in costs or prices; or significant adverse effects on competition, employment, investment, productivity, innovation, or on the ability of United States-based companies to compete with foreign based companies in domestic and import markets. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 7853 The Unfunded Mandates Reform Act of 1995 This rule will not result in an annual expenditure of $100 million or more by State, local, or tribal governments, or by the private sector and it will not significantly or uniquely affect small governments. Executive Order 12866: Regulatory Review The Department of State does not consider this rule to be a ‘‘significant regulatory action’’ under Executive Order 12866, section 3(f), Regulatory Planning and Review. In addition, the Department is exempt from Executive Order 12866 except to the extent that it is promulgating regulations in conjunction with a domestic agency that are significant regulatory actions. The Department has nevertheless reviewed the regulation to ensure its consistency with the regulatory philosophy and principles set forth in that Executive Order. Executive Order 13132: Federalism This regulation 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 section 6 of Executive Order 13132, it is determined that this rule does not have sufficient federalism implications to require consultations or warrant the preparation of a federalism summary impact statement. The Paperwork Reduction Act of 1995 The final rule does not impose information collection requirements under the provisions of the Paperwork Reduction Act, 44 U.S.C., chapter 35. Final Rule The interim rule amended the Departments’ regulations at 22 CFR part 41. In view of the foregoing, the Department does not feel it necessary to amend the regulations as published in the interim rule, and the interim rule is being incorporated herein as a final rule. Dated: November 8, 2004. Maura Harty, Assistant Secretary for Consular Affairs, Department of State. [FR Doc. 05–2999 Filed 2–15–05; 8:45 am] BILLING CODE 4710–06–P E:\FR\FM\16FER1.SGM 16FER1

Agencies

[Federal Register Volume 70, Number 31 (Wednesday, February 16, 2005)]
[Rules and Regulations]
[Pages 7851-7853]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-2832]



[[Page 7851]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19447; Directorate Identifier 2004-NM-97-AD; 
Amendment 39-13976; AD 2005-04-04]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Saab Model SAAB SF340A and SAAB 340B series airplanes. This AD requires 
a one-time inspection to determine the part and serial numbers of 
certain engine vibration isolators (mounts) and the cure dates of 
certain molded assemblies incorporated in those engine mounts; and 
related corrective actions if necessary. This AD is prompted by a 
report that disbonding of the elastomer from the inner metal core and 
shim of certain engine vibration mounts has occurred within a few 
hundred hours of operation, causing heavy chafing of the engine support 
system and chafing of the fire sensor loop. We are issuing this AD to 
prevent reduced integrity of the fire-shielding capacity of the nacelle 
structure and a possible fire detector fault.

DATES: This AD becomes effective March 23, 2005.
    The incorporation by reference of a certain publication listed in 
the AD is approved by the Director of the Federal Register as of March 
23, 2005.

ADDRESSES: For service information identified in this AD, contact Saab 
Aircraft AB, SAAB Aircraft Product Support, S-581.88, Linkping, Sweden.
    You can examine this information 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: https://
www.archives.gov/federal_register/code_of_federal_regulations/ibr_
locations.html.
    Docket: The AD docket contains the proposed AD, comments, and any 
final disposition. You can examine the AD docket on the Internet at 
https://dms.dot.gov, or in person at the Docket Management Facility 
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the U.S. 
Department of Transportation, 400 Seventh Street SW., room PL-401, 
Washington, DC. This docket number is FAA-2004-19447; the directorate 
identifier for this docket is 2004-NM-97-AD.

FOR FURTHER INFORMATION CONTACT: Mike Borfitz, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2677; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39 
with an AD for all Saab Model SAAB SF340A and SAAB 340B series 
airplanes. That action, published in the Federal Register on October 
27, 2004 (69 FR 62625), proposed to require a one-time inspection to 
determine the part and serial numbers of certain engine vibration 
isolators (mounts) and the cure dates of certain molded assemblies 
incorporated in those engine mounts; and related corrective actions if 
necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment that has been 
submitted on the proposed AD.

Request To Withdraw Proposed AD

    The commenter requests that the proposed AD be withdrawn. The 
commenter states that delamination of a bonded canister (molded 
assembly) is readily apparent and would have been detected during the 
scheduled inspections recommended in the Saab maintenance program. The 
commenter also mentions that the molded assemblies have a life limit of 
5,000 flight hours, at which point those assemblies are removed from 
the airplane. The commenter notes that by the time the proposed AD is 
issued, almost three years would have passed since the affected molded 
assemblies were put into service. The commenter remarks that it is 
unlikely that any affected molded assembly remaining in the field would 
not have already been identified and removed from service during the 
regularly scheduled maintenance inspection program. The commenter 
states that, for the reasons mentioned above, the FAA needs to consider 
the timing of the proposed AD. The commenter suggests that, at this 
late date, the unsafe condition regarding the removal of molded 
assemblies subject to delamination would have resolved itself.
    We do not agree with the commenter's request to withdraw this AD. 
The procedures specified in a service bulletin are not mandatory. 
Therefore, we must issue an AD to ensure that the identified unsafe 
condition is properly addressed. Even if the current U.S.-registered 
fleet is in compliance with the requirements of this AD, the issuance 
of the rule is still necessary to ensure that any affected airplane 
that is imported and placed on the U.S. register in the future will be 
required to be in compliance as well. We also want to ensure that, if 
the subject molded assemblies are currently in an operator's spare 
parts inventory, the actions required by this AD are performed. In 
addition, as provided by paragraph (e) of this AD, operators who have 
already done all of the actions required by this AD are already in 
compliance with this AD, and no further action is required by them. 
Furthermore, the requirements of this AD include a general visual 
inspection for chafing of the nacelle structure and fire sensor loop. 
This inspection is necessary because chafing of the nacelle structure 
and fire sensor loop is part of the unsafe condition addressed by this 
AD. We must ensure that operators did this inspection and did not just 
replace the engine mounts. Also, the airworthiness authority for the 
state of design issued an airworthiness directive mandating the same 
actions required by this AD. No change has been made to this AD 
regarding this issue.

Changes to This AD

    We have added a new paragraph (g), Parts Installation, in this AD 
to clarify that, prior to the installation of an engine vibration mount 
on an airplane, the part and serial number of the engine vibration 
mount, and the cure date of the molded assembly incorporated in the 
engine mount must be determined, and any applicable corrective action 
accomplished before further flight, in accordance with the requirements 
of paragraph (f) of this AD. Although this was our intent in the 
proposed AD, the Parts Installation paragraph was inadvertently omitted 
from the proposed AD. The subsequent paragraphs in this AD have been 
reidentified accordingly.
    Also, for clarification purposes, certain terminology in the 
proposed AD has been changed in this AD. The phrase ``molded assembly 
engine mounts (isolators)'' has been changed to ``engine vibration 
isolators (mounts).'' The term ``bonded canister assemblies''

[[Page 7852]]

has been changed to ``molded assemblies.''

Conclusion

    We have carefully reviewed the available data, including the 
comment that has been submitted, and determined that air safety and the 
public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    This AD affects about 170 airplanes of U.S. registry. The required 
actions will take about 2 work hours per airplane, at an average labor 
rate of $65 per work hour. Based on these figures, the estimated cost 
of this AD for U.S. operators is $22,100 or $130 per airplane.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    (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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD. See the ADDRESSES section for a location to 
examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2005-04-04 SAAB Aircraft AB: Amendment 39-13976. Docket No. FAA-
2004-19447; Directorate Identifier 2004-NM-97-AD.

Effective Date

    (a) This AD becomes effective March 23, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Model SAAB SF340A and SAAB 340B 
series airplanes, certificated in any category.

Unsafe Condition

    (d) This AD was prompted by a report that disbonding of the 
elastomer from the inner metal core and shim of certain engine 
vibration isolators (mounts) has occurred within a few hundred hours 
of operation, causing heavy chafing of the engine support system and 
chafing of the fire sensor loop. We are issuing this AD to prevent 
reduced integrity of the fire-shielding capacity of the engine 
nacelle structure and a possible fire detector fault.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Inspection

    (f) Within 500 flight hours after the effective date of this AD, 
perform a one-time inspection to determine the part and serial 
numbers of certain engine vibration mounts, and the cure dates of 
certain molded assemblies incorporated in those engine mounts; and a 
general visual inspection for chafing of the nacelle structure and 
fire sensor loop; and related corrective actions, as applicable; in 
accordance with the Accomplishment Instructions of Saab Service 
Bulletin 340-71-059, dated May 16, 2003. Corrective actions must be 
accomplished prior to further flight.


    Note 1: Saab Service Bulletin 340-71-059 refers to Barry 
Controls Service Letter 93948-71-05, dated April 30, 2003, as an 
additional source of service information.


    Note 2: For the purposes of this AD, a general visual inspection 
is ``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 from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normal available lighting 
conditions such as daylight, hangar lighting, flashlight or 
droplight 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.''

Parts Installation

    (g) As of the effective date of this AD, no person may install 
on any airplane an engine vibration mount unless the part and serial 
number of the engine vibration mount, and the cure date of the 
molded assembly incorporated in the engine mount, have been 
determined and any applicable corrective action accomplished before 
further flight, in accordance with the requirements of paragraph (f) 
of this AD.

Alternative Methods of Compliance (AMOCs)

    (h) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.

Related Information

    (i) Swedish airworthiness directive SAD 1-192, dated May 16, 
2003, also addresses the subject of this AD.

Material Incorporated by Reference

    (j) You must use Saab Service Bulletin 340-71-059, dated May 16, 
2003, including Attachment 1, dated April 30, 2003; to perform the 
actions that are required by this AD, unless the AD specifies 
otherwise. The Director of the Federal Register approves the 
incorporation by reference of this document in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51. For copies of the service 
information, contact Saab Aircraft AB, SAAB Aircraft Product 
Support, S-581.88, Linkoping, Sweden. For information on the 
availability of this material at the National Archives and Records 
Administration (NARA), call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.
    You may view the AD docket at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street, SW.,

[[Page 7853]]

room PL-401, Nassif Building, Washington, DC.

    Issued in Renton, Washington, on January 31, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-2832 Filed 2-15-05; 8:45 am]
BILLING CODE 4910-13-P

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