Airworthiness Directives; Saab AB, Saab Aeronautics (Type Certificate Previously Held by Saab AB, Saab Aerosystems) Airplanes, 61996-61998 [2016-20711]

Download as PDF 61996 Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Rules and Regulations constitutes terminating action for the repetitive detailed inspections required by paragraph (g)(1) of this AD for that airplane. (j) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–53–1281, dated July 29, 2014; or Airbus Service Bulletin A320–53–1281, Revision 01, dated December 1, 2014. This service information is not incorporated by reference in this AD. Lhorne on DSK30JT082PROD with RULES (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0259, dated December 5, 2014, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2015–5814. VerDate Sep<11>2014 15:15 Sep 07, 2016 Jkt 238001 (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A320–53–1281, Revision 02, including Appendix 01, dated October 9, 2015. (ii) Airbus Service Bulletin A320–53–1287, dated July 29, 2014. (3) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet https://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference 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/cfr/ibrlocations.html. Issued in Renton, Washington, on August 24, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–21144 Filed 9–7–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6668; Directorate Identifier 2014–NM–149–AD; Amendment 39–18627; AD 2016–17–14] RIN 2120–AA64 Airworthiness Directives; Saab AB, Saab Aeronautics (Type Certificate Previously Held by Saab AB, Saab Aerosystems) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Saab AB, Saab Aeronautics Model SAAB 2000 airplanes. This AD was SUMMARY: PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 prompted by a report that on some airplanes, during the paint removal process for repainting the airplane, the basic corrosion protection (anodizing and primer) coating was sanded down to bare metal on the aluminum skin panels, and the bare metal might not have been treated correctly for corrosion prevention. This AD requires an inspection of structural components of the airplane for any damaged protective coating; inspections of those areas for pitting corrosion, if necessary; a thickness measurement to determine if there is reduced skin thickness, if necessary; and repair, if necessary. We are issuing this AD to detect and correct damaged protective coatings. This condition could result in pitting corrosion damage; and reduced metal thickness, which could result in reduced static and fatigue strength of the airplane’s structural parts. DATES: This AD is effective October 13, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 13, 2016. ADDRESSES: For service information identified in this final rule, contact Saab AB, Saab Aeronautics, SE–581 88, ¨ Linkoping, Sweden; telephone +46 13 18 5591; fax +46 13 18 4874; email saab2000.techsupport@saabgroup.com; Internet https://www.saabgroup.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6668. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6668; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647– 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aerospace E:\FR\FM\08SER1.SGM 08SER1 Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Rules and Regulations Engineer, International Branch, ANM– 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227– 1112; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Lhorne on DSK30JT082PROD with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Saab AB, Saab Aeronautics Model SAAB 2000 airplanes. The NPRM published in the Federal Register on May 13, 2016 (81 FR 29807) (‘‘the NPRM’’). The NPRM was prompted by a report that on some airplanes, during the paint removal process for repainting the airplane, the basic corrosion protection (anodizing and primer) coating was sanded down to bare metal on the aluminum skin panels, and the bare metal might not have been treated correctly for corrosion prevention. The NPRM proposed to require an inspection of structural components of the airplane for any damaged protective coating; inspections of those areas for pitting corrosion, if necessary; a thickness measurement to determine if there is reduced skin thickness, if necessary; and repair, if necessary. We are issuing this AD to detect and correct damaged protective coatings. This condition could result in pitting corrosion damage; and reduced metal thickness, which could result in reduced static and fatigue strength of the airplane’s structural parts. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0160, dated July 9, 2014 (Correction: July 9, 2014) (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Saab AB, Saab Aeronautics Model SAAB 2000 airplanes. The MCAI states: SAAB received evidence that on a number of SAAB 2000 aeroplanes, during paint removal before repainting, the basic corrosion protection anodizing and primer were removed. In these cases, the basic corrosion protection coating was sanded down to bare metal on the aluminium [aluminum] skin panel in spite of existing instruction(s) contained in the Structural Repair Manual (SRM) which prohibit(s) exposing the aluminium bare metal. Due to the fact that the skin panels are manufactured from aluminium without a protective covering (unclad), the anodizing and primer is the corner stone of the aeroplane corrosion protection system. If the anodizing and primer is removed and the aluminium surface is not correctly treated, pitting corrosion may occur. In addition, sanding to VerDate Sep<11>2014 15:15 Sep 07, 2016 Jkt 238001 bare metal can inadvertently lead to metal removal and subsequently reduce the static and fatigue strength of the aeroplane structural parts. This condition, if not detected and corrected, could result in corrosion damage and/or reduced structural strength of the aeroplane structure. To address this potential unsafe condition, SAAB issued SB 2000–51–002 to provide inspection instructions. For the reasons described above, this [EASA] AD requires a one-time [detailed] inspection [for damage] * * * of required anticorrosion protective coating [e.g., bonding primer], [detailed] inspection for pitting corrosion (if necessary) [, a dye penetrant inspection for pitting corrosion (if necessary)] and measure the skin thickness (if necessary) [to determine if there is reduced skin thickness] and, depending on findings, corrective action(s) [e.g., repair]. This [EASA] AD is re-issued to correct typographical error of the effective date. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6668. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed, except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 We reviewed Saab Service Bulletin 2000–51–002, Revision 01, dated May 23, 2014. This service information describes procedures for an inspection of structural components of the airplane for any damaged protective coating; inspections of those areas for pitting corrosion; a thickness measurement to determine if there is reduced skin thickness; and repair. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 8 airplanes of U.S. registry. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 61997 We also estimate that it takes about 20 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $13,600, or $1,700 per product. In addition, we estimate that any necessary follow-on actions will take about 45 work-hours, for a cost of $3,825 per product. We have no way of determining the number of aircraft that might need these actions. We have received no definitive data that will enable us to provide cost estimates for the parts cost of the follow-on actions specified in this AD. 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 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 the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. 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. E:\FR\FM\08SER1.SGM 08SER1 61998 Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Rules and Regulations 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, 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: ■ 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): ■ 2016–17–14 Saab AB, Saab Aeronautics (Type Certificate previously held by Saab AB, Saab Aerosystems): Amendment 39–18627; Docket No. FAA–2016–6668; Directorate Identifier 2014–NM–149–AD. (a) Effective Date This AD is effective October 13, 2016. (b) Affected ADs None. (c) Applicability This AD applies to Saab AB, Saab Aeronautics (Type Certificate previously held by Saab AB, Saab Aerosystems) Model SAAB 2000 airplanes, certificated in any category, all manufacturer serial numbers, excluding the airplanes specified in paragraphs (c)(1) and (c)(2) of this AD. (1) Those airplanes identified in Table 1 of Saab Service Bulletin 2000–51–002, Revision 01, dated May 23, 2014, on which an applicable ‘‘Related Statement’’ identified in Table 1 was accomplished. (2) Those airplanes that either have retained the original paint or have been repainted by Saab AB, Saab Aeronautics. Lhorne on DSK30JT082PROD with RULES (d) Subject Air Transport Association (ATA) of America Code 51, Standard Practices/ Structures. (e) Reason This AD was prompted by a report that on some airplanes, during the paint removal process for repainting the airplane, the basic corrosion protection (anodizing and primer) coating was sanded down to bare metal on the aluminum skin panels, and the bare metal might not have been treated correctly for corrosion prevention. We are issuing this AD to detect and correct damaged protective coatings. This condition could result in pitting corrosion damage; and reduced metal thickness, which could result in reduced static and fatigue strength of the airplane’s structural parts. VerDate Sep<11>2014 15:15 Sep 07, 2016 Jkt 238001 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection, Related Investigative Actions, and Corrective Action (1) Within 2,000 flight hours or 12 months after the effective date of this AD, whichever occurs first: Do a detailed inspection of the airplane structural parts to detect damaged protective coating (e.g., bonding primer), in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000– 51–002, Revision 01, dated May 23, 2014. If any damaged protective coating is found, before further flight, do a detailed inspection of the airplane structural parts to detect pitting corrosion and, if no pitting corrosion is found, do a dye penetrant inspection of the airplane structural parts to detect pitting corrosion and a thickness measurement to determine if there is reduced skin thickness, as applicable, in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000–51–002, Revision 01, dated May 23, 2014. (2) If, during any inspection required by paragraph (g)(1) of this AD, any damage (such as pitting corrosion or damaged primer) or reduced skin thickness is detected, as defined in Saab Service Bulletin 2000–51– 002, Revision 01, dated May 23, 2014, before further flight, contact the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Saab AB, Saab Aeronautics’ EASA Design Organization Approval (DOA) for a repair method, and do the repair within the compliance time indicated in those instructions. (h) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Saab Service Bulletin 2000–51–002, dated April 9, 2014, which is not incorporated by reference in this AD. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1112; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. PO 00000 Frm 00018 Fmt 4700 Sfmt 9990 (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Saab AB, Saab Aeronautics’ EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0160, dated July 9, 2014 (Correction: July 9, 2014), for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–6668. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (k)(3) and (k)(4) of this AD. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Saab Service Bulletin 2000–51–002, Revision 01, dated May 23, 2014. (ii) Reserved. (3) For service information identified in this AD, contact Saab AB, Saab Aeronautics, ¨ SE–581 88, Linkoping, Sweden; telephone +46 13 18 5591; fax +46 13 18 4874; email saab2000.techsupport@saabgroup.com; Internet https://www.saabgroup.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference 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/cfr/ibrlocations.html. Issued in Renton, Washington, on August 18, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–20711 Filed 9–7–16; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\08SER1.SGM 08SER1

Agencies

[Federal Register Volume 81, Number 174 (Thursday, September 8, 2016)]
[Rules and Regulations]
[Pages 61996-61998]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-20711]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6668; Directorate Identifier 2014-NM-149-AD; 
Amendment 39-18627; AD 2016-17-14]
RIN 2120-AA64


Airworthiness Directives; Saab AB, Saab Aeronautics (Type 
Certificate Previously Held by Saab AB, Saab Aerosystems) Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Saab AB, Saab Aeronautics Model SAAB 2000 airplanes. This AD was 
prompted by a report that on some airplanes, during the paint removal 
process for repainting the airplane, the basic corrosion protection 
(anodizing and primer) coating was sanded down to bare metal on the 
aluminum skin panels, and the bare metal might not have been treated 
correctly for corrosion prevention. This AD requires an inspection of 
structural components of the airplane for any damaged protective 
coating; inspections of those areas for pitting corrosion, if 
necessary; a thickness measurement to determine if there is reduced 
skin thickness, if necessary; and repair, if necessary. We are issuing 
this AD to detect and correct damaged protective coatings. This 
condition could result in pitting corrosion damage; and reduced metal 
thickness, which could result in reduced static and fatigue strength of 
the airplane's structural parts.

DATES: This AD is effective October 13, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 13, 
2016.

ADDRESSES: For service information identified in this final rule, 
contact Saab AB, Saab Aeronautics, SE-581 88, Link[ouml]ping, Sweden; 
telephone +46 13 18 5591; fax +46 13 18 4874; email 
saab2000.techsupport@saabgroup.com; Internet https://www.saabgroup.com. 
You may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221. It 
is also available on the Internet at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2016-6668.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6668; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (telephone 
800-647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aerospace

[[Page 61997]]

Engineer, International Branch, ANM-116, Transport Airplane 
Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
telephone 425-227-1112; fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Saab AB, Saab 
Aeronautics Model SAAB 2000 airplanes. The NPRM published in the 
Federal Register on May 13, 2016 (81 FR 29807) (``the NPRM''). The NPRM 
was prompted by a report that on some airplanes, during the paint 
removal process for repainting the airplane, the basic corrosion 
protection (anodizing and primer) coating was sanded down to bare metal 
on the aluminum skin panels, and the bare metal might not have been 
treated correctly for corrosion prevention. The NPRM proposed to 
require an inspection of structural components of the airplane for any 
damaged protective coating; inspections of those areas for pitting 
corrosion, if necessary; a thickness measurement to determine if there 
is reduced skin thickness, if necessary; and repair, if necessary. We 
are issuing this AD to detect and correct damaged protective coatings. 
This condition could result in pitting corrosion damage; and reduced 
metal thickness, which could result in reduced static and fatigue 
strength of the airplane's structural parts.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0160, dated July 9, 2014 (Correction: July 
9, 2014) (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for certain Saab AB, Saab Aeronautics Model SAAB 2000 
airplanes. The MCAI states:

    SAAB received evidence that on a number of SAAB 2000 aeroplanes, 
during paint removal before repainting, the basic corrosion 
protection anodizing and primer were removed. In these cases, the 
basic corrosion protection coating was sanded down to bare metal on 
the aluminium [aluminum] skin panel in spite of existing 
instruction(s) contained in the Structural Repair Manual (SRM) which 
prohibit(s) exposing the aluminium bare metal. Due to the fact that 
the skin panels are manufactured from aluminium without a protective 
covering (unclad), the anodizing and primer is the corner stone of 
the aeroplane corrosion protection system. If the anodizing and 
primer is removed and the aluminium surface is not correctly 
treated, pitting corrosion may occur. In addition, sanding to bare 
metal can inadvertently lead to metal removal and subsequently 
reduce the static and fatigue strength of the aeroplane structural 
parts.
    This condition, if not detected and corrected, could result in 
corrosion damage and/or reduced structural strength of the aeroplane 
structure.
    To address this potential unsafe condition, SAAB issued SB 2000-
51-002 to provide inspection instructions.
    For the reasons described above, this [EASA] AD requires a one-
time [detailed] inspection [for damage] * * * of required 
anticorrosion protective coating [e.g., bonding primer], [detailed] 
inspection for pitting corrosion (if necessary) [, a dye penetrant 
inspection for pitting corrosion (if necessary)] and measure the 
skin thickness (if necessary) [to determine if there is reduced skin 
thickness] and, depending on findings, corrective action(s) [e.g., 
repair].
    This [EASA] AD is re-issued to correct typographical error of 
the effective date.

    You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6668.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD as proposed, except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed Saab Service Bulletin 2000-51-002, Revision 01, dated 
May 23, 2014. This service information describes procedures for an 
inspection of structural components of the airplane for any damaged 
protective coating; inspections of those areas for pitting corrosion; a 
thickness measurement to determine if there is reduced skin thickness; 
and repair. This service information is reasonably available because 
the interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 8 airplanes of U.S. registry.
    We also estimate that it takes about 20 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD on U.S. operators to be $13,600, or $1,700 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 45 work-hours, for a cost of $3,825 per product. We have no 
way of determining the number of aircraft that might need these 
actions. We have received no definitive data that will enable us to 
provide cost estimates for the parts cost of the follow-on actions 
specified in this AD.

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 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 the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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.

[[Page 61998]]

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, 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):

2016-17-14 Saab AB, Saab Aeronautics (Type Certificate previously 
held by Saab AB, Saab Aerosystems): Amendment 39-18627; Docket No. 
FAA-2016-6668; Directorate Identifier 2014-NM-149-AD.

(a) Effective Date

    This AD is effective October 13, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Saab AB, Saab Aeronautics (Type Certificate 
previously held by Saab AB, Saab Aerosystems) Model SAAB 2000 
airplanes, certificated in any category, all manufacturer serial 
numbers, excluding the airplanes specified in paragraphs (c)(1) and 
(c)(2) of this AD.
    (1) Those airplanes identified in Table 1 of Saab Service 
Bulletin 2000-51-002, Revision 01, dated May 23, 2014, on which an 
applicable ``Related Statement'' identified in Table 1 was 
accomplished.
    (2) Those airplanes that either have retained the original paint 
or have been repainted by Saab AB, Saab Aeronautics.

(d) Subject

    Air Transport Association (ATA) of America Code 51, Standard 
Practices/Structures.

(e) Reason

    This AD was prompted by a report that on some airplanes, during 
the paint removal process for repainting the airplane, the basic 
corrosion protection (anodizing and primer) coating was sanded down 
to bare metal on the aluminum skin panels, and the bare metal might 
not have been treated correctly for corrosion prevention. We are 
issuing this AD to detect and correct damaged protective coatings. 
This condition could result in pitting corrosion damage; and reduced 
metal thickness, which could result in reduced static and fatigue 
strength of the airplane's structural parts.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspection, Related Investigative Actions, and Corrective Action

    (1) Within 2,000 flight hours or 12 months after the effective 
date of this AD, whichever occurs first: Do a detailed inspection of 
the airplane structural parts to detect damaged protective coating 
(e.g., bonding primer), in accordance with the Accomplishment 
Instructions of Saab Service Bulletin 2000-51-002, Revision 01, 
dated May 23, 2014. If any damaged protective coating is found, 
before further flight, do a detailed inspection of the airplane 
structural parts to detect pitting corrosion and, if no pitting 
corrosion is found, do a dye penetrant inspection of the airplane 
structural parts to detect pitting corrosion and a thickness 
measurement to determine if there is reduced skin thickness, as 
applicable, in accordance with the Accomplishment Instructions of 
Saab Service Bulletin 2000-51-002, Revision 01, dated May 23, 2014.
    (2) If, during any inspection required by paragraph (g)(1) of 
this AD, any damage (such as pitting corrosion or damaged primer) or 
reduced skin thickness is detected, as defined in Saab Service 
Bulletin 2000-51-002, Revision 01, dated May 23, 2014, before 
further flight, contact the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the European Aviation Safety 
Agency (EASA); or Saab AB, Saab Aeronautics' EASA Design 
Organization Approval (DOA) for a repair method, and do the repair 
within the compliance time indicated in those instructions.

(h) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(g) of this AD, if those actions were performed before the effective 
date of this AD using Saab Service Bulletin 2000-51-002, dated April 
9, 2014, which is not incorporated by reference in this AD.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Shahram 
Daneshmandi, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1112; fax 425-227-1149. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Saab AB, Saab 
Aeronautics' EASA Design Organization Approval (DOA). If approved by 
the DOA, the approval must include the DOA-authorized signature.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0160, dated July 9, 2014 
(Correction: July 9, 2014), for related information. This MCAI may 
be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2016-6668.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (k)(3) and (k)(4) of this AD.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Saab Service Bulletin 2000-51-002, Revision 01, dated May 
23, 2014.
    (ii) Reserved.
    (3) For service information identified in this AD, contact Saab 
AB, Saab Aeronautics, SE-581 88, Link[ouml]ping, Sweden; telephone 
+46 13 18 5591; fax +46 13 18 4874; email 
saab2000.techsupport@saabgroup.com; Internet https://www.saabgroup.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference 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/cfr/ibr-locations.html.

    Issued in Renton, Washington, on August 18, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-20711 Filed 9-7-16; 8:45 am]
 BILLING CODE 4910-13-P