81 FR 61996 - Airworthiness Directives; Saab AB, Saab Aeronautics (Type Certificate Previously Held by Saab AB, Saab Aerosystems) Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 174 (September 8, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 174 (September 8, 2016)
| Page Range | 61996-61998 | |
| FR Document | 2016-20711 |
[Federal Register Volume 81, Number 174 (Thursday, September 8, 2016)] [Rules and Regulations] [Pages 61996-61998] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-20711] ----------------------------------------------------------------------- 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 [email protected]; Internet http://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 http://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 http://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 http://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: [email protected]. 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 http://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 [email protected]; Internet http://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: http://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
![61996 Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Rules and Regulations
constitutes terminating action for the (2) Service information identified in this prompted by a report that on some
repetitive detailed inspections required by AD that is not incorporated by reference is airplanes, during the paint removal
paragraph (g)(1) of this AD for that airplane. available at the addresses specified in process for repainting the airplane, the
paragraphs (m)(3) and (m)(4) of this AD.
(j) Credit for Previous Actions basic corrosion protection (anodizing
This paragraph provides credit for actions (m) Material Incorporated by Reference and primer) coating was sanded down
required by paragraph (i) of this AD, if those (1) The Director of the Federal Register to bare metal on the aluminum skin
actions were performed before the effective approved the incorporation by reference panels, and the bare metal might not
date of this AD using Airbus Service Bulletin (IBR) of the service information listed in this have been treated correctly for corrosion
A320–53–1281, dated July 29, 2014; or paragraph under 5 U.S.C. 552(a) and 1 CFR prevention. This AD requires an
Airbus Service Bulletin A320–53–1281, part 51. inspection of structural components of
Revision 01, dated December 1, 2014. This (2) You must use this service information
service information is not incorporated by
the airplane for any damaged protective
as applicable to do the actions required by
reference in this AD. coating; inspections of those areas for
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320–53–1281, pitting corrosion, if necessary; a
(k) Other FAA AD Provisions thickness measurement to determine if
Revision 02, including Appendix 01, dated
The following provisions also apply to this October 9, 2015. there is reduced skin thickness, if
AD: (ii) Airbus Service Bulletin A320–53–1287, necessary; and repair, if necessary. We
(1) Alternative Methods of Compliance dated July 29, 2014. are issuing this AD to detect and correct
(AMOCs): The Manager, International (3) For service information identified in
Branch, ANM–116, Transport Airplane
damaged protective coatings. This
this AD, contact Airbus, Airworthiness condition could result in pitting
Directorate, FAA, has the authority to Office—EIAS, 1 Rond Point Maurice
approve AMOCs for this AD, if requested corrosion damage; and reduced metal
Bellonte, 31707 Blagnac Cedex, France;
using the procedures found in 14 CFR 39.19. thickness, which could result in
telephone +33 5 61 93 36 96; fax +33 5 61
In accordance with 14 CFR 39.19, send your 93 44 51; email account.airworth-eas@ reduced static and fatigue strength of
request to your principal inspector or local airbus.com; Internet http://www.airbus.com. the airplane’s structural parts.
Flight Standards District Office, as (4) You may view this service information DATES: This AD is effective October 13,
appropriate. If sending information directly
to the International Branch, send it to ATTN:
at the FAA, Transport Airplane Directorate, 2016.
1601 Lind Avenue SW., Renton, WA. For The Director of the Federal Register
Sanjay Ralhan, Aerospace Engineer,
information on the availability of this approved the incorporation by reference
International Branch, ANM–116, Transport
material at the FAA, call 425–227–1221. of a certain publication listed in this AD
Airplane Directorate, FAA, 1601 Lind
(5) You may view this service information
Avenue SW., Renton, WA 98057–3356; as of October 13, 2016.
that is incorporated by reference at the
telephone 425–227–1405; fax 425–227–1149. ADDRESSES: For service information
National Archives and Records
Information may be emailed to: 9-ANM-116- identified in this final rule, contact Saab
Administration (NARA). For information on
AMOC-REQUESTS@faa.gov. Before using
the availability of this material at NARA, call AB, Saab Aeronautics, SE–581 88,
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal 202–741–6030, or go to: http:// Linköping, Sweden; telephone +46 13
inspector, the manager of the local flight www.archives.gov/federal-register/cfr/ibr- 18 5591; fax +46 13 18 4874; email
standards district office/certificate holding locations.html. saab2000.techsupport@saabgroup.com;
district office. The AMOC approval letter Issued in Renton, Washington, on August Internet http://www.saabgroup.com.
must specifically reference this AD. 24, 2016. You may view this referenced service
(2) Contacting the Manufacturer: For any John P. Piccola, Jr., information at the FAA, Transport
requirement in this AD to obtain corrective Airplane Directorate, 1601 Lind Avenue
Acting Manager, Transport Airplane
actions from a manufacturer, the action must
Directorate, Aircraft Certification Service. SW., Renton, WA. For information on
be accomplished using a method approved
by the Manager, International Branch, ANM– [FR Doc. 2016–21144 Filed 9–7–16; 8:45 am] the availability of this material at the
116, Transport Airplane Directorate, FAA; or BILLING CODE 4910–13–P FAA, call 425–227–1221. It is also
the EASA; or Airbus’s EASA DOA. If available on the Internet at http://
approved by the DOA, the approval must www.regulations.gov by searching for
include the DOA-authorized signature. DEPARTMENT OF TRANSPORTATION and locating Docket No. FAA–2016–
(3) Required for Compliance (RC): If any 6668.
service information contains procedures or Federal Aviation Administration
tests that are identified as RC, those Examining the AD Docket
procedures and tests must be done to comply You may examine the AD docket on
14 CFR Part 39
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
the Internet at http://
[Docket No. FAA–2016–6668; Directorate
procedures and tests that are not identified Identifier 2014–NM–149–AD; Amendment
www.regulations.gov by searching for
as RC may be deviated from using accepted 39–18627; AD 2016–17–14] and locating Docket No. FAA–2016–
methods in accordance with the operator’s 6668; or in person at the Docket
maintenance or inspection program without RIN 2120–AA64 Management Facility between 9 a.m.
obtaining approval of an AMOC, provided and 5 p.m., Monday through Friday,
the procedures and tests identified as RC can Airworthiness Directives; Saab AB, except Federal holidays. The AD docket
be done and the airplane can be put back in Saab Aeronautics (Type Certificate contains this AD, the regulatory
an airworthy condition. Any substitutions or Previously Held by Saab AB, Saab
changes to procedures or tests identified as
evaluation, any comments received, and
Aerosystems) Airplanes other information. The street address for
RC require approval of an AMOC.
AGENCY: Federal Aviation the Docket Office (telephone 800–647–
(l) Related Information 5527) is Docket Management Facility,
Administration (FAA), Department of
(1) Refer to Mandatory Continuing Transportation (DOT). U.S. Department of Transportation,
Lhorne on DSK30JT082PROD with RULES
Airworthiness Information (MCAI) EASA Docket Operations, M–30, West
Airworthiness Directive 2014–0259, dated ACTION: Final rule.
Building Ground Floor, Room W12–140,
December 5, 2014, for related information.
This MCAI may be found in the AD docket SUMMARY: We are adopting a new 1200 New Jersey Avenue SE.,
on the Internet at http://www.regulations.gov airworthiness directive (AD) for certain Washington, DC 20590.
by searching for and locating Docket No. Saab AB, Saab Aeronautics Model FOR FURTHER INFORMATION CONTACT:
FAA–2015–5814. SAAB 2000 airplanes. This AD was Shahram Daneshmandi, Aerospace
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![Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Rules and Regulations 61997
Engineer, International Branch, ANM– bare metal can inadvertently lead to metal We also estimate that it takes about 20
116, Transport Airplane Directorate, removal and subsequently reduce the static work-hours per product to comply with
FAA, 1601 Lind Avenue SW., Renton, and fatigue strength of the aeroplane the basic requirements of this AD. The
structural parts.
WA 98057–3356; telephone 425–227– This condition, if not detected and
average labor rate is $85 per work-hour.
1112; fax 425–227–1149. corrected, could result in corrosion damage Based on these figures, we estimate the
SUPPLEMENTARY INFORMATION: and/or reduced structural strength of the cost of this AD on U.S. operators to be
aeroplane structure. $13,600, or $1,700 per product.
Discussion To address this potential unsafe condition, In addition, we estimate that any
We issued a notice of proposed SAAB issued SB 2000–51–002 to provide necessary follow-on actions will take
rulemaking (NPRM) to amend 14 CFR inspection instructions.
For the reasons described above, this
about 45 work-hours, for a cost of
part 39 by adding an AD that would $3,825 per product. We have no way of
[EASA] AD requires a one-time [detailed]
apply to certain Saab AB, Saab inspection [for damage] * * * of required determining the number of aircraft that
Aeronautics Model SAAB 2000 anticorrosion protective coating [e.g., might need these actions. We have
airplanes. The NPRM published in the bonding primer], [detailed] inspection for received no definitive data that will
Federal Register on May 13, 2016 (81 pitting corrosion (if necessary) [, a dye enable us to provide cost estimates for
FR 29807) (‘‘the NPRM’’). The NPRM penetrant inspection for pitting corrosion (if the parts cost of the follow-on actions
was prompted by a report that on some necessary)] and measure the skin thickness
specified in this AD.
airplanes, during the paint removal (if necessary) [to determine if there is
reduced skin thickness] and, depending on Authority for This Rulemaking
process for repainting the airplane, the findings, corrective action(s) [e.g., repair].
basic corrosion protection (anodizing This [EASA] AD is re-issued to correct Title 49 of the United States Code
and primer) coating was sanded down typographical error of the effective date. specifies the FAA’s authority to issue
to bare metal on the aluminum skin rules on aviation safety. Subtitle I,
You may examine the MCAI in the
panels, and the bare metal might not section 106, describes the authority of
AD docket on the Internet at http://
have been treated correctly for corrosion the FAA Administrator. ‘‘Subtitle VII:
www.regulations.gov by searching for
prevention. The NPRM proposed to Aviation Programs,’’ describes in more
and locating Docket No. FAA–2016–
require an inspection of structural detail the scope of the Agency’s
6668.
components of the airplane for any authority.
damaged protective coating; inspections Comments
We are issuing this rulemaking under
of those areas for pitting corrosion, if We gave the public the opportunity to the authority described in ‘‘Subtitle VII,
necessary; a thickness measurement to participate in developing this AD. We Part A, Subpart III, Section 44701:
determine if there is reduced skin received no comments on the NPRM or General requirements.’’ Under that
thickness, if necessary; and repair, if on the determination of the cost to the section, Congress charges the FAA with
necessary. We are issuing this AD to public. promoting safe flight of civil aircraft in
detect and correct damaged protective air commerce by prescribing regulations
coatings. This condition could result in Conclusion
for practices, methods, and procedures
pitting corrosion damage; and reduced We reviewed the relevant data and the Administrator finds necessary for
metal thickness, which could result in determined that air safety and the safety in air commerce. This regulation
reduced static and fatigue strength of public interest require adopting this AD is within the scope of that authority
the airplane’s structural parts. as proposed, except for minor editorial because it addresses an unsafe condition
The European Aviation Safety Agency changes. We have determined that these that is likely to exist or develop on
(EASA), which is the Technical Agent minor changes: products identified in this rulemaking
for the Member States of the European • Are consistent with the intent that
action.
Union, has issued EASA Airworthiness was proposed in the NPRM for
Directive 2014–0160, dated July 9, 2014 correcting the unsafe condition; and Regulatory Findings
(Correction: July 9, 2014) (referred to • Do not add any additional burden
after this as the Mandatory Continuing upon the public than was already We determined that this AD will not
Airworthiness Information, or ‘‘the proposed in the NPRM. have federalism implications under
MCAI’’), to correct an unsafe condition Executive Order 13132. This AD will
Related Service Information Under 1 not have a substantial direct effect on
for certain Saab AB, Saab Aeronautics CFR Part 51
Model SAAB 2000 airplanes. The MCAI the States, on the relationship between
states: We reviewed Saab Service Bulletin the national government and the States,
2000–51–002, Revision 01, dated May or on the distribution of power and
SAAB received evidence that on a number 23, 2014. This service information responsibilities among the various
of SAAB 2000 aeroplanes, during paint
describes procedures for an inspection levels of government.
removal before repainting, the basic
corrosion protection anodizing and primer of structural components of the airplane For the reasons discussed above, I
were removed. In these cases, the basic for any damaged protective coating; certify that this AD:
corrosion protection coating was sanded inspections of those areas for pitting 1. Is not a ‘‘significant regulatory
down to bare metal on the aluminium corrosion; a thickness measurement to action’’ under Executive Order 12866;
[aluminum] skin panel in spite of existing determine if there is reduced skin
instruction(s) contained in the Structural 2. Is not a ‘‘significant rule’’ under the
thickness; and repair. This service
Repair Manual (SRM) which prohibit(s) DOT Regulatory Policies and Procedures
information is reasonably available
exposing the aluminium bare metal. Due to (44 FR 11034, February 26, 1979);
because the interested parties have
the fact that the skin panels are manufactured 3. Will not affect intrastate aviation in
access to it through their normal course
Lhorne on DSK30JT082PROD with RULES
from aluminium without a protective Alaska; and
covering (unclad), the anodizing and primer of business or by the means identified
is the corner stone of the aeroplane corrosion in the ADDRESSES section. 4. Will not have a significant
protection system. If the anodizing and economic impact, positive or negative,
Costs of Compliance on a substantial number of small entities
primer is removed and the aluminium
surface is not correctly treated, pitting We estimate that this AD affects 8 under the criteria of the Regulatory
corrosion may occur. In addition, sanding to airplanes of U.S. registry. Flexibility Act.
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List of Subjects in 14 CFR Part 39 (f) Compliance (2) Contacting the Manufacturer: For any
Comply with this AD within the requirement in this AD to obtain corrective
Air transportation, Aircraft, Aviation compliance times specified, unless already actions from a manufacturer, the action must
safety, Incorporation by reference, done. be accomplished using a method approved
Safety. by the Manager, International Branch, ANM–
(g) Inspection, Related Investigative Actions,
Adoption of the Amendment and Corrective Action 116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(1) Within 2,000 flight hours or 12 months
Accordingly, under the authority (EASA); or Saab AB, Saab Aeronautics’ EASA
after the effective date of this AD, whichever
delegated to me by the Administrator, occurs first: Do a detailed inspection of the Design Organization Approval (DOA). If
the FAA amends 14 CFR part 39 as airplane structural parts to detect damaged approved by the DOA, the approval must
follows: protective coating (e.g., bonding primer), in include the DOA-authorized signature.
accordance with the Accomplishment
(j) Related Information
PART 39—AIRWORTHINESS Instructions of Saab Service Bulletin 2000–
DIRECTIVES 51–002, Revision 01, dated May 23, 2014. If (1) Refer to Mandatory Continuing
any damaged protective coating is found, Airworthiness Information (MCAI) EASA
before further flight, do a detailed inspection Airworthiness Directive 2014–0160, dated
■ 1. The authority citation for part 39 of the airplane structural parts to detect
continues to read as follows: July 9, 2014 (Correction: July 9, 2014), for
pitting corrosion and, if no pitting corrosion related information. This MCAI may be
Authority: 49 U.S.C. 106(g), 40113, 44701. is found, do a dye penetrant inspection of the
airplane structural parts to detect pitting found in the AD docket on the Internet at
§ 39.13 [Amended] corrosion and a thickness measurement to http://www.regulations.gov by searching for
determine if there is reduced skin thickness, and locating Docket No. FAA–2016–6668.
■ 2. The FAA amends § 39.13 by adding as applicable, in accordance with the (2) Service information identified in this
the following new airworthiness Accomplishment Instructions of Saab Service AD that is not incorporated by reference is
directive (AD): Bulletin 2000–51–002, Revision 01, dated available at the addresses specified in
May 23, 2014. paragraphs (k)(3) and (k)(4) of this AD.
2016–17–14 Saab AB, Saab Aeronautics (2) If, during any inspection required by
(Type Certificate previously held by paragraph (g)(1) of this AD, any damage (such (k) Material Incorporated by Reference
Saab AB, Saab Aerosystems): as pitting corrosion or damaged primer) or
Amendment 39–18627; Docket No. (1) The Director of the Federal Register
reduced skin thickness is detected, as
FAA–2016–6668; Directorate Identifier approved the incorporation by reference
defined in Saab Service Bulletin 2000–51–
2014–NM–149–AD. 002, Revision 01, dated May 23, 2014, before (IBR) of the service information listed in this
further flight, contact the Manager, paragraph under 5 U.S.C. 552(a) and 1 CFR
(a) Effective Date
International Branch, ANM–116, Transport part 51.
This AD is effective October 13, 2016. Airplane Directorate, FAA; or the European (2) You must use this service information
(b) Affected ADs Aviation Safety Agency (EASA); or Saab AB, as applicable to do the actions required by
Saab Aeronautics’ EASA Design Organization this AD, unless this AD specifies otherwise.
None. Approval (DOA) for a repair method, and do (i) Saab Service Bulletin 2000–51–002,
(c) Applicability the repair within the compliance time Revision 01, dated May 23, 2014.
indicated in those instructions.
This AD applies to Saab AB, Saab (ii) Reserved.
Aeronautics (Type Certificate previously held (h) Credit for Previous Actions (3) For service information identified in
by Saab AB, Saab Aerosystems) Model SAAB This paragraph provides credit for actions this AD, contact Saab AB, Saab Aeronautics,
2000 airplanes, certificated in any category, required by paragraph (g) of this AD, if those SE–581 88, Linköping, Sweden; telephone
all manufacturer serial numbers, excluding actions were performed before the effective +46 13 18 5591; fax +46 13 18 4874; email
the airplanes specified in paragraphs (c)(1) date of this AD using Saab Service Bulletin saab2000.techsupport@saabgroup.com;
and (c)(2) of this AD. 2000–51–002, dated April 9, 2014, which is Internet http://www.saabgroup.com.
(1) Those airplanes identified in Table 1 of not incorporated by reference in this AD. (4) You may view this service information
Saab Service Bulletin 2000–51–002, Revision
01, dated May 23, 2014, on which an (i) Other FAA AD Provisions at the FAA, Transport Airplane Directorate,
applicable ‘‘Related Statement’’ identified in The following provisions also apply to this 1601 Lind Avenue SW., Renton, WA. For
Table 1 was accomplished. AD: information on the availability of this
(2) Those airplanes that either have (1) Alternative Methods of Compliance material at the FAA, call 425–227–1221.
retained the original paint or have been (AMOCs): The Manager, International (5) You may view this service information
repainted by Saab AB, Saab Aeronautics. Branch, ANM–116, Transport Airplane that is incorporated by reference at the
Directorate, FAA, has the authority to National Archives and Records
(d) Subject approve AMOCs for this AD, if requested Administration (NARA). For information on
Air Transport Association (ATA) of using the procedures found in 14 CFR 39.19. the availability of this material at NARA, call
America Code 51, Standard Practices/ In accordance with 14 CFR 39.19, send your 202–741–6030, or go to: http://
Structures. request to your principal inspector or local
www.archives.gov/federal-register/cfr/ibr-
Flight Standards District Office, as
(e) Reason locations.html.
appropriate. If sending information directly
This AD was prompted by a report that on to the International Branch, send it to ATTN: Issued in Renton, Washington, on August
some airplanes, during the paint removal Shahram Daneshmandi, Aerospace Engineer, 18, 2016.
process for repainting the airplane, the basic International Branch, ANM–116, Transport
corrosion protection (anodizing and primer) Airplane Directorate, FAA, 1601 Lind Dorr M. Anderson,
coating was sanded down to bare metal on Avenue SW., Renton, WA 98057–3356; Acting Manager, Transport Airplane
the aluminum skin panels, and the bare telephone 425–227–1112; fax 425–227–1149. Directorate, Aircraft Certification Service.
metal might not have been treated correctly Information may be emailed to: 9-ANM-116- [FR Doc. 2016–20711 Filed 9–7–16; 8:45 am]
Lhorne on DSK30JT082PROD with RULES
for corrosion prevention. We are issuing this AMOC-REQUESTS@faa.gov. Before using
BILLING CODE 4910–13–P
AD to detect and correct damaged protective any approved AMOC, notify your appropriate
coatings. This condition could result in principal inspector, or lacking a principal
pitting corrosion damage; and reduced metal inspector, the manager of the local flight
thickness, which could result in reduced standards district office/certificate holding
static and fatigue strength of the airplane’s district office. The AMOC approval letter
structural parts. must specifically reference this AD.
VerDate Sep<11>2014 15:15 Sep 07, 2016 Jkt 238001 PO 00000 Frm 00018 Fmt 4700 Sfmt 9990 E:\FR\FM\08SER1.SGM 08SER1](https://thefederalregister.org/doc/81_FR_62170/page/3.svg)
Document Created: 2018-02-09 13:12:39
Document Modified: 2018-02-09 13:12:39
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective October 13, 2016. | |
| Contact | 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. | |
| FR Citation | 81 FR 61996 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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