Airworthiness Directives; Saab Model SAAB 2000 Airplanes, 49173-49174 [05-16456]

Download as PDF Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21341; Directorate Identifier 2003–NM–026–AD; Amendment 39–14231; AD 2005–17–10] RIN 2120–AA64 Airworthiness Directives; Saab Model SAAB 2000 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Saab Model SAAB 2000 airplanes. This AD requires an inspection for cracking of the fastener holes in the front and rear spars, a modification of the fastener holes of the front and rear spars and the rear spar web, and related investigative/ corrective actions if necessary. This AD is prompted by a report of cracking of certain fastener holes in the lower spar cap of the rear spar and in the lower skin at the front spar. We are issuing this AD to prevent cracking of the front and rear spars, which could result in fuel leakage and consequent reduced structural integrity of the wing structure. DATES: This AD becomes effective September 27, 2005. The incorporation by reference of a certain publication listed in the AD is approved by the Director of the Federal Register as of September 27, 2005. ADDRESSES: For service information identified in this AD, contact Saab Aircraft AB, SAAB Aircraft Product ¨ Support, S–581.88, Linkoping, Sweden. 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–2005–21341; the directorate identifier for this docket is 2003–NM– 026–AD. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington VerDate jul<14>2003 16:13 Aug 22, 2005 Jkt 205001 98055–4056; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with an AD for certain Saab Model SAAB 2000 airplanes. That action, published in the Federal Register on June 3, 2005 (70 FR 32540), proposed to require an inspection for cracking of the fastener holes in the front and rear spars, a modification of the fastener holes of the front and rear spars and the rear spar web, and related investigative/ corrective actions if necessary. New Relevant Service Information Saab has issued Service Bulletin 2000–57–038, Revision 01, dated June 24, 2004. The proposed AD refers to Saab Service Bulletin 2000–57–038, dated December 18, 2002, as the acceptable source of service information for doing the proposed actions. The procedures in Revision 01 of the service bulletin are essentially the same as those in the original issue. Therefore, we have revised paragraphs (f) and (g) of this AD to refer to Revision 01 of the service bulletin as the appropriate source of service information for doing the actions required by those paragraphs. We have also added a new paragraph (h) to this AD (and reidentified subsequent paragraphs accordingly) to give credit for actions done before the effective date of this AD in accordance with the original issue of the service bulletin. Comments We provided the public the opportunity to participate in the development of this AD. No comments have been submitted on the proposed AD or on the determination of the cost to the public. Explanation of Change to Applicability The FAA has revised the applicability of this AD to identify model designations as published in the most recent type certificate data sheet for the affected models. Conclusion We have carefully reviewed the available data, 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 3 airplanes of U.S. registry. The required actions (inspections and modification) will take PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 49173 about 250 work hours per airplane, at an average labor rate of $65 per work hour. Required parts will cost about $8,557 per airplane. Based on these figures, the estimated cost of this AD for U.S. operators is $74,421, or $24,807 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 Accordingly, under the authority delegated to me by the Administrator, I E:\FR\FM\23AUR1.SGM 23AUR1 49174 Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Rules and Regulations the FAA amends 14 CFR part 39 as follows: 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] further flight, contact the Manager, International Branch, ANM–116, for further actions, or the LFV (or its delegated agent). If any scratches or other damage is detected on the skin surface or the surface of the front spar, before further flight, repair in accordance with a method approved by the Manager, International Branch, ANM–116, or the LFV (or its delegated agent). Actions Accomplished Previously 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): I 2005–17–10 SAAB Aircraft AB: Amendment 39–14231. Docket No. FAA–2005–21341; Directorate Identifier 2003–NM–026–AD. Effective Date (a) This AD becomes effective September 27, 2005. Affected ADs (b) None. Applicability (c) This AD applies to certain Saab Model SAAB 2000 airplanes having serial numbers 004 through 063 inclusive, certificated in any category. Unsafe Condition (d) This AD was prompted by a report of cracking of certain fastener holes in the lower spar cap of the rear spar and in the lower skin at the front spar. We are issuing this AD to prevent cracking of the front and rear spars, which could result in fuel leakage and consequent reduced structural integrity of the wing structure. 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) Prior to the accumulation of 20,000 total flight cycles, perform non-destructive tests for cracking of the fastener holes in the lower spar cap of the rear spar and in the lower skin at the left-hand and right-hand sides of the front spar, between WS20 and WS83 inclusive; by accomplishing all the actions specified in Parts A, B, and C of the Accomplishment Instructions of Saab Service Bulletin 2000–57–038, Revision 01, dated June 24, 2004. If any cracking is detected, before further flight, repair the cracking according to a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the Luftfartsverket (LFV) (or its delegated agent). 16:13 Aug 22, 2005 Jkt 205001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–19865; Directorate Identifier 2003–NM–242–AD; Amendment 39–14230; AD 2005–17–09] RIN 2120–AA64 (h) Inspections or modifications accomplished before the effective date of this AD in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000– 57–038, dated December 18, 2002, are considered acceptable for compliance with the corresponding actions specified in this AD. Airworthiness Directives; Boeing Model 747, 757, 767 and 777 Series Airplanes Alternative Methods of Compliance (AMOCs) SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747, 757, 767, and 777 series airplanes. That AD currently requires modifying certain drip shields located on the flight deck, and follow-on actions. This new AD removes certain airplanes that are included in the applicability statement of the existing AD, and requires modifying additional drip shields on the flight deck of certain other airplanes. This AD is prompted by a determination that certain airplanes have drip shields that are not adequately resistant to fire. We are issuing this AD to prevent potential ignition of the moisture barrier cover of the drip shield, which could propagate a small fire that results from an electrical arc, leading to a larger fire. DATES: This AD becomes effective September 27, 2005. The incorporation by reference of certain publications listed in the AD is approved by the Director of the Federal Register as of September 27, 2005. On February 2, 2001 (65 FR 82901, December 29, 2000), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. 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 (i) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Material Incorporated by Reference (j) You must use Saab Service Bulletin 2000–57–038, Revision 01, dated June 24, 2004, 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. To get copies of the service information, contact Saab Aircraft AB, SAAB Aircraft Product ¨ Support, S–581.88, Linkoping, Sweden. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https://www.archives.gov/federalregister/cfr/ibr-locations.html. Issued in Renton, Washington, on August 11, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–16456 Filed 8–22–05; 8:45 am] BILLING CODE 4910–13–P Modification (g) Prior to the accumulation of 20,000 total flight cycles, modify the fastener holes of the front and rear spars and the rear spar web, including related investigative actions, by accomplishing all the actions specified in Part D of the Accomplishment Instructions of Saab Service Bulletin 2000–57–038, Revision 01, dated June 24, 2004. If 1⁄4-inch fasteners are needed for holes No. 7 and No. 8, before VerDate jul<14>2003 DEPARTMENT OF TRANSPORTATION PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: E:\FR\FM\23AUR1.SGM 23AUR1

Agencies

[Federal Register Volume 70, Number 162 (Tuesday, August 23, 2005)]
[Rules and Regulations]
[Pages 49173-49174]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-16456]



[[Page 49173]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21341; Directorate Identifier 2003-NM-026-AD; 
Amendment 39-14231; AD 2005-17-10]
RIN 2120-AA64


Airworthiness Directives; Saab Model SAAB 2000 Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Saab Model SAAB 2000 airplanes. This AD requires an inspection 
for cracking of the fastener holes in the front and rear spars, a 
modification of the fastener holes of the front and rear spars and the 
rear spar web, and related investigative/corrective actions if 
necessary. This AD is prompted by a report of cracking of certain 
fastener holes in the lower spar cap of the rear spar and in the lower 
skin at the front spar. We are issuing this AD to prevent cracking of 
the front and rear spars, which could result in fuel leakage and 
consequent reduced structural integrity of the wing structure.

DATES: This AD becomes effective September 27, 2005.
    The incorporation by reference of a certain publication listed in 
the AD is approved by the Director of the Federal Register as of 
September 27, 2005.

ADDRESSES: For service information identified in this AD, contact Saab 
Aircraft AB, SAAB Aircraft Product Support, S-581.88, Link[ouml]ping, 
Sweden.
    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-2005-21341; the directorate 
identifier for this docket is 2003-NM-026-AD.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with an AD for certain Saab Model SAAB 2000 airplanes. That action, 
published in the Federal Register on June 3, 2005 (70 FR 32540), 
proposed to require an inspection for cracking of the fastener holes in 
the front and rear spars, a modification of the fastener holes of the 
front and rear spars and the rear spar web, and related investigative/ 
corrective actions if necessary.

New Relevant Service Information

    Saab has issued Service Bulletin 2000-57-038, Revision 01, dated 
June 24, 2004. The proposed AD refers to Saab Service Bulletin 2000-57-
038, dated December 18, 2002, as the acceptable source of service 
information for doing the proposed actions. The procedures in Revision 
01 of the service bulletin are essentially the same as those in the 
original issue. Therefore, we have revised paragraphs (f) and (g) of 
this AD to refer to Revision 01 of the service bulletin as the 
appropriate source of service information for doing the actions 
required by those paragraphs. We have also added a new paragraph (h) to 
this AD (and re-identified subsequent paragraphs accordingly) to give 
credit for actions done before the effective date of this AD in 
accordance with the original issue of the service bulletin.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been submitted on the proposed 
AD or on the determination of the cost to the public.

Explanation of Change to Applicability

    The FAA has revised the applicability of this AD to identify model 
designations as published in the most recent type certificate data 
sheet for the affected models.

Conclusion

    We have carefully reviewed the available data, 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 3 airplanes of U.S. registry. The required 
actions (inspections and modification) will take about 250 work hours 
per airplane, at an average labor rate of $65 per work hour. Required 
parts will cost about $8,557 per airplane. Based on these figures, the 
estimated cost of this AD for U.S. operators is $74,421, or $24,807 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,

[[Page 49174]]

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):

2005-17-10 SAAB Aircraft AB: Amendment 39-14231. Docket No. FAA-
2005-21341; Directorate Identifier 2003-NM-026-AD.

Effective Date

    (a) This AD becomes effective September 27, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to certain Saab Model SAAB 2000 airplanes 
having serial numbers 004 through 063 inclusive, certificated in any 
category.

Unsafe Condition

    (d) This AD was prompted by a report of cracking of certain 
fastener holes in the lower spar cap of the rear spar and in the 
lower skin at the front spar. We are issuing this AD to prevent 
cracking of the front and rear spars, which could result in fuel 
leakage and consequent reduced structural integrity of the wing 
structure.

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) Prior to the accumulation of 20,000 total flight cycles, 
perform non-destructive tests for cracking of the fastener holes in 
the lower spar cap of the rear spar and in the lower skin at the 
left-hand and right-hand sides of the front spar, between WS20 and 
WS83 inclusive; by accomplishing all the actions specified in Parts 
A, B, and C of the Accomplishment Instructions of Saab Service 
Bulletin 2000-57-038, Revision 01, dated June 24, 2004. If any 
cracking is detected, before further flight, repair the cracking 
according to a method approved by the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the Luftfartsverket 
(LFV) (or its delegated agent).

Modification

    (g) Prior to the accumulation of 20,000 total flight cycles, 
modify the fastener holes of the front and rear spars and the rear 
spar web, including related investigative actions, by accomplishing 
all the actions specified in Part D of the Accomplishment 
Instructions of Saab Service Bulletin 2000-57-038, Revision 01, 
dated June 24, 2004. If \1/4\-inch fasteners are needed for holes 
No. 7 and No. 8, before further flight, contact the Manager, 
International Branch, ANM-116, for further actions, or the LFV (or 
its delegated agent). If any scratches or other damage is detected 
on the skin surface or the surface of the front spar, before further 
flight, repair in accordance with a method approved by the Manager, 
International Branch, ANM-116, or the LFV (or its delegated agent).

Actions Accomplished Previously

    (h) Inspections or modifications accomplished before the 
effective date of this AD in accordance with the Accomplishment 
Instructions of Saab Service Bulletin 2000-57-038, dated December 
18, 2002, are considered acceptable for compliance with the 
corresponding actions specified in this AD.

Alternative Methods of Compliance (AMOCs)

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

Material Incorporated by Reference

    (j) You must use Saab Service Bulletin 2000-57-038, Revision 01, 
dated June 24, 2004, 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. To 
get copies of the service information, contact Saab Aircraft AB, 
SAAB Aircraft Product Support, S-581.88, Link[ouml]ping, Sweden. To 
view the AD docket, go to the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., room PL-401, 
Nassif Building, Washington, DC. To review copies of the service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at the 
NARA, call (202) 741-6030, or go to https://www.archives.gov/federal-
register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on August 11, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-16456 Filed 8-22-05; 8:45 am]
BILLING CODE 4910-13-P

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