81 FR 62022 - Airworthiness Directives; The Boeing Company 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 | 62022-62024 | |
| FR Document | 2016-21148 |
[Federal Register Volume 81, Number 174 (Thursday, September 8, 2016)] [Proposed Rules] [Pages 62022-62024] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-21148] ======================================================================== Proposed Rules Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. ======================================================================== Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Proposed Rules [[Page 62022]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9068; Directorate Identifier 2016-NM-067-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This proposed AD was prompted by reports of cracks in horizontal stabilizer lower skins. This proposed AD would require repetitive inspections for cracking of the horizontal stabilizer lower skin, and corrective actions if necessary. This proposed AD also provides actions that would terminate certain repetitive inspections. We are proposing this AD to detect and correct cracks in horizontal stabilizer lower skins resulting in reduced local stiffness of the horizontal stabilizer, which can cause heavy vibration leading to loss of structural integrity of the horizontal stabilizer. DATES: We must receive comments on this proposed AD by October 24, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.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-2016-9068. 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- 9068; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Gaetano Settineri, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6577; fax: 425-917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-9068; Directorate Identifier 2016-NM-067-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received reports of approximately 90 cracks in horizontal stabilizer lower skins with most of them occurring between stabilizer station (SSTA) 111.10 and 166.30. Ten operators reported cracks on 18 airplanes outside this range with 14 of them inboard of SSTA 111.10. The cracks range in length from 0.25 inch to 3.75 inches, and the airplanes had between 12,670 and 69,569 total flight cycles. The cracks started on the outer surface of the horizontal stabilizer lower skin where the chem-milled edge aligns with the edge of the lower flange of the rear spar. The cracks grew parallel to the rear spar. High secondary bending stresses due to compression buckling of the skins and sonic fatigue can cause the cracks to grow. Cracks have also started from the fastener line nearest the chem-milled step. This horizontal stabilizer lower skin cracking, if not corrected, could result in reduced local stiffness of the horizontal stabilizer, which can cause heavy vibration leading to loss of structural integrity of the horizontal stabilizer. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Special Attention Service Bulletin 737-55-1059, Revision 1, dated April 6, 2016 (``SASB 737-55-1059 R1''). The service information describes procedures for doing inspections of the horizontal stabilizer lower skin, and repairs. The service information also describes procedures for doing actions that would terminate certain repetitive inspections. 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. FAA's Determination We are proposing this AD because we evaluated all the relevant information [[Page 62023]] and determined the unsafe condition described previously is likely to exist or develop in other products of these same type designs. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ``Differences Between this Proposed AD and the Service Information. For information on the procedures and compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-9068. The phrase ``related investigative actions'' is used in this proposed AD. Related investigative actions are follow-on actions that (1) are related to the primary action, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ``corrective actions'' is used in this proposed AD. Corrective actions correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information SASB 737-55-1059 R1, specifies to contact the manufacturer for certain instructions, but this proposed AD would require accomplishment of repair methods, modification deviations, and alteration deviations in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 270 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection....................... 4 work-hours x $85 $0 $340 per inspection $91,800 per per hour = $340 per cycle. inspection cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- Estimated Costs for Optional Actions ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Modification........................... Up to 51 work-hours per $721 Up to $5,056 per stabilizer x $85 per hour = stabilizer. $4,335. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these repairs: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Skin slice repair........................ Up to 438 work-hours x $85 $0 Up to $37,230. per hour = $37,230. External doubler repair.................. 26 work-hours x $85 per $0 $2,210. hour = $2,210. ---------------------------------------------------------------------------------------------------------------- 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: (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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: [[Page 62024]] 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): The Boeing Company: Docket No. FAA-2016-9068; Directorate Identifier 2016-NM-067-AD. (a) Comments Due Date We must receive comments by October 24, 2016. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 737-300, -400, and - 500 series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 737-55-1059, Revision 1, dated April 6, 2016 (``SASB 737-55-1059 R1''). (d) Subject Air Transport Association (ATA) of America Code 55; Horizontal stabilizer. (e) Unsafe Condition This AD was prompted by reports of cracks in horizontal stabilizer lower skins. We are issuing this AD to detect and correct cracks in horizontal stabilizer lower skins resulting in reduced local stiffness of the stabilizer, which can cause heavy vibration leading to loss of structural integrity of the horizontal stabilizer. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections, Related Investigative Actions, and Corrective Actions for Group 1, Configuration 1 Airplanes For Group 1, Configuration 1 airplanes, as identified in SASB 737-55-1059 R1: Except as specified in paragraph (i)(1) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of SASB 737-55-1059 R1, do a detailed inspection for cracking of the horizontal stabilizer lower skin; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of SASB 737-55-1059 R1, except as specified in paragraph (i)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection of the horizontal stabilizer lower skin, if applicable, thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of SASB 737-55-1059 R1. Options specified in SASB 737-55-1059 R1, for accomplishing the inspections are acceptable for the corresponding requirements of this paragraph provided that the inspections are done at the applicable times in paragraph 1.E., ``Compliance,'' of the SASB 737-55-1059 R1. (h) Inspections, Related Investigative Actions, and Corrective Actions for Group 1, Configuration 2 Airplanes For Group 1, Configuration 2 airplanes, as identified in SASB 737-55-1059 R1: Except as specified in paragraph (i)(1) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of SASB 737-55-1059 R1, do the actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of SASB 737-55-1059 R1, except as specified in paragraph (i)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, if applicable, thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of SASB 737-55-1059 R1. Options specified in SASB 737-55-1059 R1, for accomplishing the inspections are acceptable for the corresponding requirements of this paragraph provided that the inspections are done at the applicable times in paragraph 1.E., ``Compliance,'' of SASB 737-55- 1059 R1. (1) Do a high frequency eddy current inspection for cracking of the skin around any repair done as specified in the structural repair manual or any external doubler repair, and a detailed inspection for any loose or any missing fastener of repaired doublers. (2) Do a detailed inspection for cracking of the inspar lower skin of the horizontal stabilizer in unrepaired areas. (3) Do a low frequency eddy current inspection for cracking of the forward fastener row of any external doubler repair. (i) Service Information Exceptions (1) Where SASB 737-55-1059 R1, specifies a compliance time ``after the Revision 1 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) If any cracking, corrosion, hole elongation, or loose or missing fastener is found during any inspection required by this AD, and SASB 737-55-1059 R1, specifies to contact Boeing for repair instructions: Before further flight, repair the cracking, corrosion, hole elongation, loose or missing fasteners using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office, 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 manager of the ACO, send it to the attention of the person identified in paragraph (k)(1) of this AD. Information may be emailed to: [email protected]. (2) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (k) Related Information (1) For more information about this AD, contact Gaetano Settineri, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6577; fax: 425-917-6590; email: [email protected]. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544- 5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.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. Issued in Renton, Washington, on August 24, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-21148 Filed 9-7-16; 8:45 am] BILLING CODE 4910-13-P
![62022
Proposed Rules Federal Register
Vol. 81, No. 174
Thursday, September 8, 2016
This section of the FEDERAL REGISTER p.m., Monday through Friday, except proposed AD because of those
contains notices to the public of the proposed Federal holidays. comments.
issuance of rules and regulations. The For service information identified in We will post all comments we
purpose of these notices is to give interested this NPRM, contact Boeing Commercial receive, without change, to http://
persons an opportunity to participate in the Airplanes, Attention: Data & Services www.regulations.gov, including any
rule making prior to the adoption of the final personal information you provide. We
rules.
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone will also post a report summarizing each
206–544–5000, extension 1; fax 206– substantive verbal contact we receive
DEPARTMENT OF TRANSPORTATION 766–5680; Internet https:// about this proposed AD.
www.myboeingfleet.com. You may view Discussion
Federal Aviation Administration this referenced service information at
the FAA, Transport Airplane We have received reports of
14 CFR Part 39 Directorate, 1601 Lind Avenue SW., approximately 90 cracks in horizontal
Renton, WA. For information on the stabilizer lower skins with most of them
[Docket No. FAA–2016–9068; Directorate occurring between stabilizer station
Identifier 2016–NM–067–AD] availability of this material at the FAA,
call 425–227–1221. It is also available (SSTA) 111.10 and 166.30. Ten
RIN 2120–AA64 on the Internet at http:// operators reported cracks on 18
www.regulations.gov by searching for airplanes outside this range with 14 of
Airworthiness Directives; The Boeing and locating Docket No. FAA–2016– them inboard of SSTA 111.10. The
Company Airplanes 9068. cracks range in length from 0.25 inch to
3.75 inches, and the airplanes had
AGENCY: Federal Aviation Examining the AD Docket between 12,670 and 69,569 total flight
Administration (FAA), DOT.
You may examine the AD docket on cycles.
ACTION: Notice of proposed rulemaking The cracks started on the outer
(NPRM). the Internet at http://
www.regulations.gov by searching for surface of the horizontal stabilizer lower
SUMMARY: We propose to adopt a new and locating Docket No. FAA–2016– skin where the chem-milled edge aligns
airworthiness directive (AD) for certain 9068; or in person at the Docket with the edge of the lower flange of the
The Boeing Company Model 737–300, Management Facility between 9 a.m. rear spar. The cracks grew parallel to the
–400, and –500 series airplanes. This and 5 p.m., Monday through Friday, rear spar. High secondary bending
proposed AD was prompted by reports except Federal holidays. The AD docket stresses due to compression buckling of
of cracks in horizontal stabilizer lower contains this proposed AD, the the skins and sonic fatigue can cause the
skins. This proposed AD would require regulatory evaluation, any comments cracks to grow. Cracks have also started
repetitive inspections for cracking of the received, and other information. The from the fastener line nearest the chem-
horizontal stabilizer lower skin, and street address for the Docket Office milled step.
(phone: 800–647–5527) is in the This horizontal stabilizer lower skin
corrective actions if necessary. This
ADDRESSES section. Comments will be
cracking, if not corrected, could result
proposed AD also provides actions that
available in the AD docket shortly after in reduced local stiffness of the
would terminate certain repetitive
receipt. horizontal stabilizer, which can cause
inspections. We are proposing this AD
heavy vibration leading to loss of
to detect and correct cracks in FOR FURTHER INFORMATION CONTACT:
structural integrity of the horizontal
horizontal stabilizer lower skins Gaetano Settineri, Aerospace Engineer, stabilizer.
resulting in reduced local stiffness of Airframe Branch, ANM–120S, FAA,
the horizontal stabilizer, which can Seattle Aircraft Certification Office Related Service Information Under
cause heavy vibration leading to loss of (ACO), 1601 Lind Avenue SW., Renton, 1 CFR Part 51
structural integrity of the horizontal WA 98057–3356; phone: 425–917–6577; We reviewed Boeing Special
stabilizer. fax: 425–917–6590; email: Attention Service Bulletin 737–55–
DATES: We must receive comments on gaetano.settineri@faa.gov. 1059, Revision 1, dated April 6, 2016
this proposed AD by October 24, 2016. SUPPLEMENTARY INFORMATION: (‘‘SASB 737–55–1059 R1’’). The service
ADDRESSES: You may send comments, Comments Invited information describes procedures for
using the procedures found in 14 CFR doing inspections of the horizontal
11.43 and 11.45, by any of the following We invite you to send any written stabilizer lower skin, and repairs. The
methods: relevant data, views, or arguments about service information also describes
• Federal eRulemaking Portal: Go to this proposal. Send your comments to procedures for doing actions that would
http://www.regulations.gov. Follow the an address listed under the ADDRESSES terminate certain repetitive inspections.
section. Include ‘‘Docket No. FAA– This service information is reasonably
mstockstill on DSK3G9T082PROD with PROPOSALS
instructions for submitting comments.
• Fax: 202–493–2251. 2016–9068; Directorate Identifier 2016– available because the interested parties
• Mail: U.S. Department of NM–067–AD’’ at the beginning of your have access to it through their normal
Transportation, Docket Operations, M– comments. We specifically invite course of business or by the means
30, West Building Ground Floor, Room comments on the overall regulatory, identified in the ADDRESSES section.
W12–140, 1200 New Jersey Avenue SE., economic, environmental, and energy
Washington, DC 20590. aspects of this proposed AD. We will FAA’s Determination
• Hand Delivery: Deliver to Mail consider all comments received by the We are proposing this AD because we
address above between 9 a.m. and 5 closing date and may amend this evaluated all the relevant information
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![62024 Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Proposed Rules
Authority: 49 U.S.C. 106(g), 40113, 44701. (h) Inspections, Related Investigative of the local flight standards district office/
Actions, and Corrective Actions for Group 1, certificate holding district office.
§ 39.13 [Amended] Configuration 2 Airplanes (3) An AMOC that provides an acceptable
For Group 1, Configuration 2 airplanes, as level of safety may be used for any repair,
■ 2. The FAA amends § 39.13 by adding modification, or alteration required by this
the following new airworthiness identified in SASB 737–55–1059 R1: Except
as specified in paragraph (i)(1) of this AD, at AD if it is approved by the Boeing
directive (AD): Commercial Airplanes Organization
the applicable time specified in paragraph
The Boeing Company: Docket No. FAA– 1.E., ‘‘Compliance,’’ of SASB 737–55–1059 Designation Authorization (ODA) that has
R1, do the actions specified in paragraphs been authorized by the Manager, Seattle
2016–9068; Directorate Identifier 2016–
(h)(1), (h)(2), and (h)(3) of this AD; and do all ACO, to make those findings. To be
NM–067–AD.
applicable related investigative and approved, the repair method, modification
(a) Comments Due Date corrective actions; in accordance with the deviation, or alteration deviation must meet
Accomplishment Instructions of SASB 737– the certification basis of the airplane, and the
We must receive comments by October 24, approval must specifically refer to this AD.
2016. 55–1059 R1, except as specified in paragraph
(i)(2) of this AD. Do all applicable related (k) Related Information
(b) Affected ADs investigative and corrective actions before
(1) For more information about this AD,
None. further flight. Repeat the inspections
contact Gaetano Settineri, Aerospace
specified in paragraphs (h)(1), (h)(2), and
Engineer, Airframe Branch, ANM–120S,
(c) Applicability (h)(3) of this AD, if applicable, thereafter at
FAA, Seattle ACO, 1601 Lind Avenue SW.,
This AD applies to The Boeing Company the applicable intervals specified in
Renton, WA 98057–3356; phone: 425–917–
paragraph 1.E., ‘‘Compliance,’’ of SASB 737–
Model 737–300, –400, and –500 series 6577; fax: 425–917–6590; email:
55–1059 R1. Options specified in SASB 737–
airplanes, certificated in any category, as gaetano.settineri@faa.gov.
55–1059 R1, for accomplishing the
identified in Boeing Special Attention (2) For service information identified in
inspections are acceptable for the
Service Bulletin 737–55–1059, Revision 1, corresponding requirements of this paragraph this AD, contact Boeing Commercial
dated April 6, 2016 (‘‘SASB 737–55–1059 provided that the inspections are done at the Airplanes, Attention: Data & Services
R1’’). applicable times in paragraph 1.E., Management, P.O. Box 3707, MC 2H–65,
‘‘Compliance,’’ of SASB 737–55–1059 R1. Seattle, WA 98124–2207; telephone 206–
(d) Subject 544–5000, extension 1; fax 206–766–5680;
(1) Do a high frequency eddy current
Air Transport Association (ATA) of inspection for cracking of the skin around Internet https://www.myboeingfleet.com. You
America Code 55; Horizontal stabilizer. any repair done as specified in the structural may view this referenced service information
repair manual or any external doubler repair, at the FAA, Transport Airplane Directorate,
(e) Unsafe Condition and a detailed inspection for any loose or any 1601 Lind Avenue SW., Renton, WA. For
This AD was prompted by reports of cracks missing fastener of repaired doublers. information on the availability of this
in horizontal stabilizer lower skins. We are (2) Do a detailed inspection for cracking of material at the FAA, call 425–227–1221.
issuing this AD to detect and correct cracks the inspar lower skin of the horizontal Issued in Renton, Washington, on August
in horizontal stabilizer lower skins resulting stabilizer in unrepaired areas. 24, 2016.
in reduced local stiffness of the stabilizer, (3) Do a low frequency eddy current John P. Piccola, Jr.,
which can cause heavy vibration leading to inspection for cracking of the forward
Acting Manager, Transport Airplane
loss of structural integrity of the horizontal fastener row of any external doubler repair.
Directorate, Aircraft Certification Service.
stabilizer. (i) Service Information Exceptions [FR Doc. 2016–21148 Filed 9–7–16; 8:45 am]
(f) Compliance (1) Where SASB 737–55–1059 R1, specifies BILLING CODE 4910–13–P
a compliance time ‘‘after the Revision 1 date
Comply with this AD within the
of this service bulletin,’’ this AD requires
compliance times specified, unless already compliance within the specified compliance
done. DEPARTMENT OF TRANSPORTATION
time after the effective date of this AD.
(g) Inspections, Related Investigative (2) If any cracking, corrosion, hole Federal Aviation Administration
Actions, and Corrective Actions for Group 1, elongation, or loose or missing fastener is
Configuration 1 Airplanes found during any inspection required by this
AD, and SASB 737–55–1059 R1, specifies to
14 CFR Part 39
For Group 1, Configuration 1 airplanes, as contact Boeing for repair instructions: Before [Docket No. FAA–2016–9056; Directorate
identified in SASB 737–55–1059 R1: Except further flight, repair the cracking, corrosion, Identifier 2016–NM–007–AD]
as specified in paragraph (i)(1) of this AD, at hole elongation, loose or missing fasteners
the applicable time specified in paragraph using a method approved in accordance with RIN 2120–AA64
1.E., ‘‘Compliance,’’ of SASB 737–55–1059 the procedures specified in paragraph (j) of
R1, do a detailed inspection for cracking of this AD. Airworthiness Directives; Saab AB,
the horizontal stabilizer lower skin; and do Saab Aeronautics (Formerly Known as
(j) Alternative Methods of Compliance Saab AB, Saab Aerosystems)
all applicable related investigative and
(AMOCs)
corrective actions; in accordance with the Airplanes
Accomplishment Instructions of SASB 737– (1) The Manager, Seattle Aircraft
55–1059 R1, except as specified in paragraph Certification Office, FAA, has the authority to AGENCY: Federal Aviation
(i)(2) of this AD. Do all applicable related approve AMOCs for this AD, if requested Administration (FAA), DOT.
investigative and corrective actions before using the procedures found in 14 CFR 39.19. ACTION: Notice of proposed rulemaking
In accordance with 14 CFR 39.19, send your (NPRM).
further flight. Repeat the inspection of the
request to your principal inspector or local
horizontal stabilizer lower skin, if applicable,
Flight Standards District Office, as SUMMARY: We propose to adopt a new
mstockstill on DSK3G9T082PROD with PROPOSALS
thereafter at the applicable intervals specified appropriate. If sending information directly
in paragraph 1.E., ‘‘Compliance,’’ of SASB airworthiness directive (AD) for certain
to the manager of the ACO, send it to the Saab AB, Saab Aeronautics Model
737–55–1059 R1. Options specified in SASB attention of the person identified in
737–55–1059 R1, for accomplishing the SAAB 2000 airplanes. This proposed
paragraph (k)(1) of this AD. Information may
inspections are acceptable for the be emailed to: 9-ANM-Seattle-ACO–AMOC- AD was prompted by an occurrence that
corresponding requirements of this paragraph Requests@faa.gov. was reported of rudder pedal restriction
provided that the inspections are done at the (2) Before using any approved AMOC, on a SAAB Model 2000 airplane with
applicable times in paragraph 1.E., notify your appropriate principal inspector, the large potable water system (LPWS)
‘‘Compliance,’’ of the SASB 737–55–1059 R1. or lacking a principal inspector, the manager installed, equipped with in-line heaters.
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Document Created: 2018-02-09 13:13:10
Document Modified: 2018-02-09 13:13:10
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by October 24, 2016. | |
| Contact | Gaetano Settineri, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6577; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 62022 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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